Prof. Debasis chakraborty

List of Major Technical Work

Prof. Chakraborty has worked 35 years in Vikram Sarabhai Space Center (VSSC), ISRO and Defence Research and Development laboratory (DRDL), DRDO on various practical aerodynamic and propulsion problems related to sounding rockets, satellite launch vehicles, strategic and tactical missiles. Computational Fluid Dynamics (CFD) was used as a tool in solving these design problems. He has used both commercial and indigenous CFD codes for providing reliable data to the designer and contributed very significantly in reducing the developmental cost and time of the mission. Indigenous CFD codes were developed and commercial CFD codes were validated extensively before using them in design exercises. Some important technical contributions are highlighted below.

A. Contribution in VSSC

A1. Aerodynamic Simulation of Heat Shield Separation Test on Ground
With no big vacuum facility in the country, the qualification of separation test of heat shield was carried out in ground and the effect of aerodynamics in the ground test was accounted through numerical simulation. The observations in the ground test were properly explained and a safe separation in the flight was predicted. This analysis resulted in a substantial good saving in terms of money and time and repeated success of safe separation of heat shield in various flights. Recently, the work has been identified as high impact work for mission analysis in VSSC

A2. Development of comprehensive flow analysis code for air intakes and propulsive nozzles
An Indigenous Euler code was developed to analyse inviscid flow in air intakes and propulsive nozzles. Comparisons of the present analysis with experimental results and the results of other theoretical calculations for conical and contoured nozzles flow field show that the software gives reasonably good prediction of the inviscid internal flow field. The software was then applied to simulate the flow field of air intake of air breathing rocket and the high area ratio nozzles of satellite launch vehicle. A survey of various types of air intakes for various missions, their theory and design principles were summarized. The developed code was used extensively in designing the intake of airbreathing sounding rockets.

A3. Development of empirical tool for estimation of plume boundary and base flows for multijet launch vehicles
An engineering tool based on empirical and analytical models has been developed to compute plume interactions, base pressures and convective heat fluxes in case the neighbouring jets of the launch vehicles interact. The obtained results agree well with experimental data and method of characteristics.
A two dimensional procedure has been described to calculate the flow parameters in the base region of the launch vehicle in the presence of propulsive jets. Mass, momentum, energy balance is ensured over the control volume in the base region alongwith Korst's escape criteria. The computed results show reasonable comparison with experimental and flight measurements. These codes were used extensively for estimating the plumes and convective base heating of ASLV, PSLV, GSLV and sounding rockets.

A4. Analytical procedure of rocket plume boundary in the presence of co-flowing supersonic stream
An analytical procedure was worked out based on supersonic potential flow theory and oblique shock relations to estimate the rocket plume boundary in the presence of coflowing external supersonic stream. Bessel function is used to arrive at integral-differential equation which has been solved numerically. The developed procedure was validated by comparing the plume boundaries obtained from experiment and other semi-empirical procedure.

A5. Numerical simulation of base flow in presence of propulsive jets.
Base flow in the presence of propulsive jet is explored numerically by solving Navier Stokes equations with k-e turbulence model. The code is validated against reliable experimental results and applied to simulate the complex multi-jet interacting flow occurring in the base region of the GSLV at different altitudes. The reverse flow parameters like temperature, pressure etc. is found to be lower than those estimated by two-dimensional semi empirical Korst model.

A6. Numerical simulation of Dual Mode RamJet (DMRJ) combustor
DMRJ combustor flow field for various ramp configurations in the strut are analysed for nonreacting mixing by 3D RANS solver PARAS3D. Two performance parameters viz, mixing efficiency and pressure recovery factors were evaluated for various cases at various axial location of the combustor from the numerical simulation results. These results guided the design of DMRJ combustor.

A7. Simulation of Ejector Ramjet combustor flowfield.
A computational study was carried out on the Ejector Ram Jet Engine to obtain an insight into the reactive flow field and to estimate the flow parameters, using commercial CFD code. The simulated results compared well against the available experimental values. The effect of heat release on entrainment and mixing process was studied.  Parametric studies on the geometry of the flow passages were also carried out and the effect on thrust augmentation factor and entrainment ratio are brought out.

A8. Direct Numerical Simulation (DNS) of reacting and nonreacting high speed mixing layers.
To understand mixing and combustion process inside scramjet combustor, spatio–temporal DNS studies were carried out for reacting and nonreacting mixing layers under confined environment. Although the geometrical model was simple, it possess all complexities of reacting environment present in scramjet combustor. A good match of computed surface pressure with experimental data forms the basis of further analysis Detailed thermochemical exploration revealed the reaction occurred mostly in braids of the vortices and the combustion is diffusive in nature. Gas dynamics effects are more predominant and compared to the chemical kinetics effect. Detailed full chemistry calculation for H2 –air system (7 step and 7 species) for three different temperatures show clearly that the chemistry is not fast and reaction is not even complete at the end of the combustor. The computed time series data was analysed to find out the predictive capability of existing combustion model to predict high speed mixing layer and it is found that empirical EDC combustion model for finite rate chemistry predict all pertinent features of reaction rate profile. It was demonstrated that simpler turbulence – chemistry interaction model is adequate to describe chemistry for high speed mixing layers, turbulence models itself require improvement.

B. Contribution in DRDL
Major responsibilities of Prof. Chakraborty in DRDL are to provide aerodynamic and propulsive design data for the ongoing and future DRDO missile using Computational Fluid Dynamics (CFD) tools. The most important contribution I have made at DRDL is to move the CFD from being a fashionable academic research tool to a useful design tool for aerodynamic and propulsive characterization of DRDO missile. An internal CFD group (Computational Combustion Dynamics (CCD) Division) was established in DRDL for numerical simulation of reacting and nonreacting turbulent flows for propulsive characterization of various ongoing and future missile projects of DRDO. The use of advanced numerical tools has reduced the dependence on the experiments in wind tunnel and other propulsion test facilities and resulted in significant reduction in developmental cost and time. Accomplishing these has needed the development of indigenous state-of-the-art CFD codes as well as the use of commercial CFD codes both of which needing periodic upgradation and validation. Because of the demonstration of usefulness of this important tool, the demand for CFD simulation is increasing even among hard core development groups who seem to want quick answers. In a few cases that I have known, the system developers are using CFD results to take stand-alone design decision without testing. My major contributions in DRDL include:

B1. Tip to Tail simulation of Hypersonic Airbreathing vehicle
To estimate overall performance parameters (mainly thrust – drag margin) of hydrocarbon fuelled (Liquid kerosene/ gaseous Ethylene) hypersonic airbreathing vehicle, coupled nonreacting (turbulent flow in the vehicle forebody and outer surface) and reacting turbulent flow (in scramjet combustor) has been carried out. All geometrical details of the vehicles including wings, fins, Single Expansion Ramp Nozzle (SERN), fuel injection struts with injection holes (~0.4 mm diameters) were considered. 3-D RANS equations are solved along with SST-k-wturbulence model. Single step chemical reaction with Lagrangian Particle Tracking Method is used for combustion of kerosene fuel. Mass flow rate of ingested air and the requirement of kerosene fuel are found to increase with the increase of angle of attack. Non-uniform distribution of CO2 and H2O mass fraction has been observed at the outlet of the combustor. Some amount of unused O2 has been observed at the core regions adjacent to the side wall, whereas, unburnt kerosene vapour has been observed at the top-side wall corners. The computed performance parameters are used to finalize the configuration as well as the mission.

B2. Design and Analysis of Scramjet combustor of Hypersonic Airbreathing vehicle:
Design and Analysis of subscale and full scale scramjet combustor with strut based kerosene fuel injection system are carried out through numerical simulations of various reacting and nonreacting flow field. Understanding of mixing and combustion behavior in the combustor has led to the relocation the struts and fuel injection system which not only resulted in optimized thrust and combustion efficiencies but also provided benign thermal environment for fuel injection strut. The CFD based design has been validated through experimental testing.  The numerical simulations acted as a guide to experimental investigation and considerable reduction of developmental cycle could be achieved. End-to-end CFD simulations of the configuration including both external and internal flows at different operating conditions are carried out. The numerical simulations acted as a guide to experimental investigation.

B3. Supersonic / Hypersonic Air Intake analysis for ramjet and scramjet applications
Supersonic/hypersonic flow field of both isolated and installed Air Intake in ramjet and scramjet powered missiles have been simulated to estimate various performance parameters (pressure recovery and mass capture ratio etc). Computational methodology was validated through comparison against wind tunnel test results for various steady and unsteady flows. The performance of installed air intake including unstarting was predicted for different supersonic and hypersonic missiles at different mach number and angle of attack. The study of unsteady flow in isolated air intake with buzz suppression mechanism predicted the effectiveness of the mechanism.  CFD results complemented wind tunnel data to determine the maximum pressure in the scramjet combustor so that intake-combustor interaction in does not occur for hypersonic airbreathing vehicle.

B4. Hypersonic Propulsion for long duration flight
DRDL has initiated the development of long range hypersonic cruise vehicle and I have been made the leader of the study team. Two different Hypersonic Cruise Missile (HCM) concepts are studied. Both ground launched and air launched versions are contemplated. For the ground launch version, hypersonic glide and fixed point scramjet operation and for air launch version Dual Combustion Ramjet (DCR) are considered as propulsion options. High lift aerodynamic configuration design, high temperature materials for airframe and scramjet combustor, descent phase trajectory and endgame are identified as some of the critical design issues to realize HCM.  In hypersonic glide and fixed Mach number scramjet operation, HCM will be mounted on top of a solid booster and boosted to desired Mach number.  In the cruise phase, the vehicle will be propelled by long duration hydrocarbon fuelled scramjet engine to the desired destination. In the descent phase, the scramjet will be switched off and the vehicle will be decelerated to Mach 2 which result in a high energy impact. Waverider concept is utilized to evolve the cruise vehicle aerodynamics and vehicle integrated scramjet combustor has been designed. Coupled external-internal CFD calculations (involving nonreacting flow in vehicle forebody and reacting CFD in scramjet combustor) were performed to estimate aero-propulsive parameters of the vehicle.  High fidelity design were carried out for thermal management of both external aerodynamic heating and exothermic reaction due to kerosene-air burning in scramjet combustor. Niobium alloy with silicide coatings, C-SiC composites, Inconel, Nimonic alloys and titanium are considered the candidate materials for combustor and air frames. The Dual Combustion Ramjet (DCR) concept which combines the advantage of both ramjet and scramjet propulsion system is considered for air launched option. DCR enhances the HCM’s air-breathing mode operation and thereby reducing the overall system weight and makes the vehicle capable of air launch.  The fuel is added in a small dump-type subsonic combustor, which acts as a fuel-rich gas generator. The hot fuel-rich exhaust is injected into the supersonic combustor and made to undergo the secondary combustion with incoming air through inlet.

B5. Evaluation of Lateral Aerodynamic Characteristics of air to air missiles
Lateral aerodynamic characteristics of different air to air missiles at critical flow conditions are evaluated to find out the cause of high rolling moment observed in the flight. Using inhouse NS solver and structured grid approach, different missile configurations are studied to find out the contribution of different missile surfaces in generating the rolling moment. It is observed that the cause of high rolling moment is due to the strong interaction of wing vortices with fin.  For accurate prediction of peak value and to obtain the real characteristic of CRM, simulations need to be carried out with proper grid and for small interval (~5o) of roll orientation.

B6. Aerodynamic characteristics helicopter launched missile with two side jets:
Aerodynamic parameters of a helicopter launched antitank missile with two side jets are estimated in complete M-α-φ-δ envelope using an indigenously developed RANS solver. The effect of plume gazing on the vehicle surface was predicted and important design changes were made based on this study. All the fins were deflected by equal angles so as to provide a net pitch-up or pitch-down moment. For Mach 0.54 at angle of attack of 20 degrees with all fins deflection at 20 degrees the windward side jet is seen to have interference with the windward fins. The variation of total normal force and pitching moment coefficients with fin deflections for higher angles of attacks show linear variation with fin deflections.

B7. Estimation of Captive Load for air to air missiles mounted on fighter aircraft.
The Captive loads at critical flow conditions have been estimated for air to air missiles by simulating the flow past a full fighter aircraft with four missiles mounted on it, using indigenous grid free Euler solver. Estimated aerodynamic loads along with the inertia loads are used for designing of launch shoes and rail. These CFD simulations were used for obtaining the certification for carrying out captive flight trial of the missile.

B8. Separation Dynamics of air to air missiles from fighter aircraft
An integrated separation dynamics suite has been used to carry out the store separation dynamics of air to air missiles missile from SU-30 aircraft at various free stream condition. The suite consists of a pre-processor (to generate the chimera cloud of nodes and their connectivity), grid-free kinetic upwind Euler solver with aerodynamic damping (to obtain the aerodynamic forces and moments) and a 6-DOF trajectory solver (to predict the trajectory including tip-off dynamics). This suite was validated with the wind tunnel tests of a generic store separating from a wing pylon. The store separation suite has been used to simulate the release of inboard and outboard missiles from the fighter aircraft at various flow conditions. Perturbation studies are also carried out to study the effect of Thrust misalignment, wing, fin misalignment etc.  It has been observed from the study that ASTRA is separating safely from SU-30 aircraft at simulated free stream conditions. The bounds of the longitudinal and lateral displacements were predicted. Numbers of release flight of ASTRA from su-30 were carried out without wind tunnel tests and the results matched with pre flight prediction. The results gave so much confidence to the test pilots that he insists for CFD results before testing the missiles in any new flight conditions. Chairman of Flight Readiness Review (FRR) of recently concluded Flight trials od ASTRA from SU-30.

B9. Integration of missile plume with separation dynamics suite
The hot plume exhaust from the missile may critically affect the skin of aircraft or electronic components in the aircraft. The plume may get ingested by the air-intake that affect the performance or lead to flame extinction. Therefore, it is important to predict the plume path during missile separation from the aircraft. Plume path along the trajectory of the missile is predicted using modified particle integration model. Flow field for isolated plume is generated using multi-species Navier Stokes solver and the missile trajectories are obtained separately for number of critical launch conditions. A cloud of particles are injected continuously from the nozzle exit as the missile traverses after separation from the aircraft, the particles are traced in the direction of their velocity. The plume path at any given instant of time  along the missile trajectory is constructed using the time to travel and corresponding missile orientation and position. The thermal interference at any point on the aircraft during missile separation is also computed.

B10. Fairing Separation studies of HSTDV Launch Vehicle
A large number of aerodynamic data has been generated for the HSTDV launch vehicle during opening and separation of nose and cylindrical panels in an efficient manner. More than 300 CFD simulations are carried out with different orientations of panels. The aerodynamic data base has been used to arrive at the scheme of panel separation and time sequence of separations of various panels and cruise vehicle. Further, pressure and force distributions are provided for structural design. CFD simulations were also carried out for the ground test conditions of RTTS, TBRL at Mach 0.6 (simulating flight dynamic pressure). Very good match of computational surface pressures and panel trajectories with the test results give confidence to the designer to use CFD data for flight tests.

B11. Characterization of Jet Vane Thrust Vector Control (TVC) Flow field
At the initial phase of mission, jet vanes can be used to meet the control requirement of the missile. The numerical prediction methodology was validated by comparing against cold flow wind tunnel jet vane test data and was applied for predicting the characterization of different missile jet vane flow field under severe thermal and mechanical load. CFD generated data has been used to develop a mathematical correlation, which provides forces and moments as a function of chamber pressure and vane deflection angles. The CFD generated correlation is used in mission analysis. Jet vane characterization has been carried out for different tactical missiles (LRSAM, AAD, SRSAM, PJ10, PRALOY, MPATGM etc.) with different  nozzle configurations, propellant compositions and duty cycles.

B12. CFD Simulation for Base Flow Analysis
The interaction of hot rocket exhaust and supersonic stream of strategic missile was simulated numerically to explain the failure of the mission. The recirculatory flow phenomena occurred in the flight was explained and the flow properties including the high gas temperature in the cavity between the rocket nozzle and base shroud were predicted at different instant of time. Predicted surface temperature in the cavity region matched well with flight-measured values.  Based on the analysis, a thermal barrier in the base region was proposed and the computations were carried out for the revised configuration.

B13.  Numerical Analysis of Ship based Vertical Hot Launcher (VHL)
Ship based VHL has been designed based on CFD. Different configurations were simulated and CFD simulation results are used to improve the preliminary design and arrive at a configuration having less backflow through active canister and lower pressure on gas gathering tank walls.  The wall heat loads and pressure load data generated by CFD are used for launcher structural and thermal analysis. In addition, a new compact and efficient design based on alternate ducting system having two side uptakes have been proposed in which all the design criteria are met.

B 14.  Kinetic Heating Analysis of missiles
Missile surface temperatures due to kinetic heating were estimated along the flight trajectory for B-05 and ASTRA missions. Convective heat fluxes obtained from detailed 3D CFD simulation for different isothermal conditions are used in 3D heat conduction solver to determine the surface temperature and good overall agreement was obtained between preflight prediction and flight measurements. Conjugate heat transfer analysis involving simultaneous simulation of fluid flow equations and heat conduction equation was first validated against reliable experimental data and applied for predicting the surface temperature of B-05 (PS-07, GS-03) and ASTRA missions. 

B 15. End to End simulation of new generation liquid fuelled and solid fuelled air breathing missiles 
For demonstrating the indigenously developed LFRJ technology, a demonstrator vehicle is configured with belly-mounted twin intake. As the flow field is highly complex, engineering methods are inadequate and detailed CFD based methods have been introduced at early stage of missile design cycle and aerodynamic characteristics of the vehicle was carried out through coupled non reacting external and internal flow solver for both design and off-design conditions. CFD data base has helped to evolve the configuration progressively. Various components like intake diverter, intake, actuator coverts, tail fins etc are modified to achieve better performance. For boron based solid fuel ducted ramjet missile (Indo-Russian Joint collaboration) SFDR, several detailed CFD studies are being performed to finalise the configuration. As Chairman of the System Engineering Committee (SEC), guidance is provided to finalize the LFRJ-TD and SFDR configurations.

B16. Simulation of RCS thruster plume and free stream interaction for Air Defence mission:
The interaction of jets from pitch, yaw, roll and divert thruster with free stream interaction has been simulated for PAD and PDV mission. The computed heat flux data is used to predict the skin temperature on the missile surface and found to be within material allowable temperature for the flight duration. This preflight prediction brought in confidence about the thermal safety of missile in presence of multi-jets and due to kinetic heating.

B17. Design of Supersonic Exhaust Diffuser (SED) for testing high altitude rocket motors.
When rocket nozzles designed for high-altitude operation are tested in ground level conditions, the exhaust gas flow separates in the divergent portion of the nozzle.  One of the simpler method to simulate high altitude test conditions is a Supersonic Exhaust Diffuser (SED) consisting of a cylindrical supersonic diffuser and a subsonic diffuser. The impingement of the rocket jet on SED wall and vacuum level in the chamber is function of nozzle throat area, duct cross sectional area, duct exit area, and ratio of the specific heats of the products of combustion. Various operating regimes of SED are first understood by exploring the experimental conditions available in literature through numerical simulation tool. Very good comparison of numerical and experimental data forms the basis of applying the numerical tool in the design of SED for testing the high altitude rocket motor. CFD studies were carried out using various tunnel geometric and gas dynamic parameters and optimal internal flow path is arrived at. CHT analysis are being carried out with various water flow rates for the thermal design of structural elements.

B18.  Development of Indigenous Large Eddy Simulation (LES) code for compressible turbulence
An indigenous Large Eddy Simulation (LES) code is developed to predict the finer characteristics of turbulence in high speed nonreacting and reacting flows pertaining to aerodynamic and propulsion problems of various missile system. A hybrid approach is adopted by coupling central difference Maccormack scheme (to treat flow in the smooth region) and upwind modified SLAU2 scheme (to treat flow near the discontinuities like shock, contact surface etc.).  The new scheme has been validated extensively for number stringent canonical problems namely, supersonic flow past forward facing step (Emery test case), supersonic flow past compression corner, hypersonic flow past cylinder, stationary compressible isentropic vortex, lid driven flow in a square cavity, Toro’s blast wave problem, shock-vortex interaction problem, subsonic and supersonic backward facing step problems, supersonic mixing layers etc. Gibbs phenomena sensor is implemented for detecting shocks and contact discontinuity and to make smooth changes from central differencing scheme to upwind scheme. An improved method of digital filtering is also implemented for providing inflow turbulence. An alternate upwind scheme namely Rotated HLL (RHLL) scheme has also been developed to enhance the applicability of the code. The code is currently being tested for practical engineering problems like shock-boundary layer interaction, intake unstarting, sonic injection in supersonic cross flows etc.

B19. Prediction methodologies for Combustion instability in Solid Rocket Motor
Activities are initiated to develop CFD capabilities to predict combustion instability in Solid rocket motor which is a demanding problem in the low smoke rocket motor. Models for unsteady combustion, two-phase flow, turbulence are being developed to be integrated with the compressible Navier-Stokes solver to address the problem of coupling of flow acoustics and combustion dynamics under a common framework. The unsteady mass flow rate formulation caused due to propellant burning is implemented through User Defined Function in an existing commercial unsteady solver.  The growth and decay pattern of the disturbances have been demonstrated and the methodology has been worked out for nozzle damping for cold flow and hot flow condition.

B20. Model Free Simulations for Compressible Mixing Layer
Confined supersonic mixing layer is explored through Direct Numerical Simulation (DNS).  Both two- and three-dimensional spatio – temporal simulations were carried out employing higher order finite difference scheme as well as finite volume scheme based on open source software (OpenFOAM) to understand the effect of three-dimensionality on the development of mixing layer.  It is observed that although the instantaneous structures exhibit three dimensional features, the average pressure and velocities are predominantly two dimensional.  The computed wall pressures match well with experimental results. Significant differences are observed for species and temperature distribution between 2D and 3D calculations, and 2D calculations do not match the experimental observation of smooth variations as reported in literature.  Reynolds stress distribution for 3D calculations show a narrower profile with less peak values compared to 2D calculations; while normal stress anisotropy is higher for 3D case.  It appears that RANS calculations with turbulence models based on isotropy may not predict the flow field correctly for higher convective Mach numbers.

B 21 Estimation of grain boundary evaluation of solid rocket motor port.
Grain boundary of solid rocket motor port is estimated through Minimum Distance Function (MDF). The internal ballistics parameters of motor ports with various grain shapes are evaluated. The grain boundaries are used for combustion instability simulation.

B 22 Steady/Unsteady simulation of solid Rocket motor port flow field.
Steady/unsteady flow field simulations are carried out in the port flow field of rocket motor to understand the flow dynamics in the port. The effect of various geometrical complexities including radial and circumferential slots are analysed to estimate the pressure field and unsteady oscillations at the motor port. Computed pressure across the width of the slots are used to study the structural integrity of the grain geometry.

B 23 Estimation of Erosive burning of Solid Rocket Motor.
The existing correlation of erosive burning for cylindrical geometry is extended to non symmetric configurations through detailed CFD data of motor port. The modified theory works very well various rocket motors with cylindrical as well as finocyl geometries. Methodology is being developed in collaboration with IISc to predict the burn rate of solid rocket motor with composite propellant. The predicted burn rates match well with published data as well as blind test cases of solid rocket motors.

B24. Plume interaction analysis with jet deflector
During missile lift off, any asymmetrical impingement of rocket plume on the jet deflector can cause severe load on the jet deflector.  If the anchoring system of the jet deflector is not adequate to withstand the load, the deflector displacement may cause severe damage to the launcher and the adjoining launch system.  CFD simulations were carried out using indigenous CERANS code to estimate the side load for different lift off position of the missile. The effect of cross wind on the flow solution is also estimated.  The computed impingement load was used in the design of the anchoring system of the missile.
For vertically launched missiles from mobile launch vehicles, rocket motor jet plume is deflected away by an inclined deflector. The metal structure of deflector is insulated from the plume by an ablative liner. It is essential that liner should not be eroded to the extent of exposing the base metal structure due to the motor plume in case of hang fire and the estimation of erosion of liner caused due to both thermal and mechanical loads are very important for structural design. Detailed CFD simulations are carried out with very fine mesh and the convective heat fluxes were computed. It was found that the erosion rate is proportional to the convective heat fluxes. The proportionality factor was calibrated with short burn rocket motor test results. The predicted erosion pattern was seen to match nicely with exact missile firing from the launch vehicles.

B25 Plume interaction with canister wall
For canister launch missiles, as the missile traverse through the canister, the hot exhaust plume from the rocket motor impinges on the canister wall and cause significant thermal and mechanical loads on the canister wall.  Accurate estimation of the pressure and heat fluxes due to plume impingement in the cansister wall for different missile positions is very much necessary for the efficient thermostructural design of the canister. Detailed three dimensional viscous CFD simulations employing very fine mesh for different missile positions are carried out to estimate pressure and thermal parameters inside the canister. The heat flux and pressure data from CFD provide the input for thermal and structural analysis of the canister.

B26      Simulation of Stage Jettisoning Flow Field
Firing of upper stage motor in the close proximity of the spent stage can create lot of disturbance to the upper stage and the event is mission critical. Design of separation sequence necessitates the accurate estimation of the flow field around the upper and the lower stages of the missile. Numerical simulations were carried out with different separation distance between the stages using in-house 3D RANS solver CERANS. For lower separation distance, a large recirculation zone in the upper stage cylindrical portion is observed while the flow is relatively clean in the upper stage for upper separation distance. A severe jet-upstream flow interaction for lower separation distance case is observed due to large momentum of flow in the transverse direction obstructing the external flow; while, the jet is coming out smoothly in the external flow zone and the plume boundary is grazing the tip of upper stage flows. CFD studies were used to determine the optimum separation distance for stage jettisioning.

B27 Simulation of Installed Air Intake Flow Field
Intake performance is a critical point in the design of ramjet and other supersonic airbreathing mission. The intake is very sensitive to the interaction with the upstream external flow and downstream combustion process and hence exhibits complex flow phenomena in its range of operation.  The performance of the individual intake gets modified when it is installed to the core body at downstream location. The variation of the performance may be very significant when the vehicle is at angle of incidence. The flowfield of the installed air intake mounted on the rear portion of a missile is analysed. The methodology has been validated against the literature results of isolated mixed compression air intake flow field and was used to predict the installed intake performance at an angle of incidence. Computed intake performances (both windward and leeward positions) match nicely with the experimental results.

B 28 Conversion of indigenous CFD codes from MPI to CUDA for GPGPU platforms
Computational Fluid Dynamics (CFD), weather prediction, chemical and nuclear reaction modeling applications are highly computational intensive, owing to the large data sets. Efforts have been made by various researchers to reduce this computation time by parallelizing these applications on high performance computing platforms.  General Purpose Graphics Processing Units (GPGPUs) provide a low cost solution to high performance computing. GPU is especially designed for problems that can be expressed as data-parallel computations, that is, same program is executed on many data elements (SPMD) in parallel. Data-parallel processing maps data elements to parallel processing threads. Application programs that process large data sets can use a data-parallel programming model to speed up the computations. Indigenous MPI CFD codes (grid free Euler (q-LSKUM) and RANS code (CERANS)) are  converted to CUDA programming to port to GPGPU platforms.

B 29 Development of Indigenous RANS solver for Aero-propulsive characterization of Aerospace vehicles
A density based three dimensional finite volume  RANS solver is developed in unstructured grid framework in CFD General Notification System (CGNS) format to solve complex aeropropulsive flows in all Mach number regime. Use of low speed preconditioning allows to handle both the incompressible and compressible flow regimes uniformly.  Turbulence is modelled through Spallart Allmaras model with compressibility correction. The developed solver is extensively verified and validated for number of canonical problems including turbulent flow over flat plate, compression corner, supersonic injection in cross flow etc. and very good match is obtained between experimental and other numerical data. The developed code is applied to understand the mixing phenomena in rectangular scramjet combustor and control phenomena of aerospace vehicle through sonic jet injection.

B 30 Simulation of DMSJ combustor flow field in wider Mach number range
Long-range Hypersonic airbreathing Cruise Missiles (HCMs) with unique combination of speed, lethality, survivability and range has the potential to revolutionize warfare by providing the armed forces with the ability to take the fight to the adversary more quickly, at greater distances, with greater firepower and with high degree of survivability. Both ground launch and air launched options of  HCM is feasible. To avoid early detection, air launch option is very attractive. For air launch option, the missile is carried to a high altitude by a powerful aircraft and is accelerated to hypersonic Mach number by a rocket booster. To keep the weight of the booster to a manageable limit, it is desirable to have a scramjet engine capable of operating in larger range of Mach number without any geometry change.In Dual Mode ScramJet (DMSJ) engine, the scramjet combustor is allowed to work in ramjet mode in the lower Mach number regime (M~4-5) by tailoring the fuel injection. The resulting heat release will form a thermal throat at a desired location to enable the combustor to work in ramjet mode. In the higher Mach number range (M>5), normal scramjet operation will continue without the occurrence of thermal throat. The transition prediction from ramjet to scramjet is very challenging and strongly depends on many factors namely; wall heat transfer, chemical kinetic. Turbulent transport properties etc. DLR Hyshot configuration is taken as a test case for validation and detailed high fidelity numerical simulations are carried out to study the effect of various chemical and physical phenomena in studying transition from ramjet combustion to scramjet combustion.

B 31 Simulation of Dual Combustion Ramjet (DCR) Engine flow field
John Hopkins Laboratory, USA proposes a new propulsion concept namely; Dual Combustion Ramjet (DCR) wherein the scramjet operation in a wider Mach number range (Mach 4-6) is feasible.In DCR engine, there exists two sets of intakes (subsonic and supersonic), subsonic dump combustor and a tandem supersonic combustor. The intakes placed in the compression field of conical fore body split the air to feed the subsonic dump combustor and supersonic dump combustor. All fuel rich gas from the gas generator enters the scramjet combustor and get heated and partially cracked. The fuel-rich effluent gases provide the core flow for mixing with the annular supersonic inlet supply in the supersonic combustor. Detailed numerical simulation has been carried out to characterize both subsonic and supersonic intakes. The effect of angle of attack and back pressure in intake flow development is systematically studied. Overall vehicle performance is estimated through end-to-end simulation (including nonreacting flow in vehicle forbody and intake and reacting flow in DCR combustor) of vehicle flow path.

B 32 Simulation of Hypersonic Airbreathing vehicle flow field in free-jet flow condition
End-to end numerical simulations(involving nonreacting simulation in vehicle outsurface and intake and reacting simulation in the scramjet combustor) of 1:1 scale hypersonic airbreathing vehicle (HSTDV) model are carried out for Central Institute of Aviation Motor (CIAM), Russia  free jet test conditions, The computational domain includes the nozzle geometry upstream of test section and diffuser system downstream of test section. High quality multi-block structured grid (~ 58 million) is generated in the computational domain. The grid near the wall is very fine to resolve velocity boundary layer as well as thermal boundary layer. The simulations were carried out for both nonreacting and reacting flows with different equivalence ratio with both gaseous ethylene and liquid kerosene fuels. The effect wall boundary conditions (adiabatic and isothermal) on flow development are systematically studied. Computed wall pressure and convective heat flux data match nicely with experimental results. 

B 33 New Software development
As Technology Director, DOCD, Guidance are being provided to the Scientists of CFD and CCD divisions to develop industry standard state-of-art CFD softwares to tackle many complex problems that are not amenable to commercial CFD software. Important progress has been made in developing grid adaptation based on flow gradients in the existing inhouse CFD solvers. The software is validated for both 2D and 3D test cases of transonic and supersonic flow. It is observed that the shocks are crisply captured after the adaptation strategy is implemented. Many advanced topics like Advanced Evaporation model, Large Eddy Simulation (LES) and Conjugate Heat Transfer (CHT) models have been added to the commercial software CFX through used defined subroutines. Computational Aeroaccoustics, Computational Aeroelasticity, Unsteady Euler solver in unstructured mesh, Erosion modeling, Reduced Chemical Kinetics for hydrocarbon – air system, Dual Mode Ramjet Scramjet (DMRJ) simulation, Transition modeling etc., are in the various stages of development in the Directorate.

technical publications and research work

A1. Refereed International Journal Publication

1. Debasis Chakraborty, H.V.Nagraja Upadhaya, P.J.Paul and H.S.Mukunda: “A Thermo-Chemical Exploration of Two Dimensional Reacting Supersonic Mixing Layer”, Physics of Fluids, Vol 9 (11), pp 3513 - 3522, 1997.
2. Debasis Chakraborty and S.Vasantha: “Aerodynamic Simulation of Heat Shield Separation Test on Ground”, The Aeronautical Journal, Vol 103, No. 1027, pp 435 - 441, September 1999.
3. Debasis Chakraborty, P. J. Paul and H. S. Mukunda: “Evaluation of Empirical Combustion Models for High Speed H2/air Confined Mixing Layer Using DNS Data", Combustion and Flame, Vol 121, pp 195 - 209, April, 2000.
4. Debasis Chakraborty, P. J. Paul and H. S. Mukunda: “Effect of Confinement on the Growth and Structure of the Supersonic Mixing Layer”, Combustion and Flame, Vol 121, pp 386 - 389, April, 2000.
5. Debasis Chakraborty, P. J. Paul and H. S. Mukunda: “Two Dimensional Direct Numerical Simulation of Non-Reacting Supersonic Confined Mixing Layer”, The Aeronautical Journal, Vol 104, No. 1036, pp 291 - 296, June 2000.
6. Debasis Chakraborty, A. P. Roychowdhury, V. Ashok and Pradeep Kumar: “Numerical investigation of staged transverse sonic injection in Mach 2 stream in confined environment” The Aeronautical Journal, Vol 107, No. 1078, pp 719 - 729, December, 2003.
7. P. Manna  and Debasis Chakraborty: “Numerical investigation of transverse sonic injection in a nonreacting supersonic combustor”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 219, No. 3, pp 205-215, 2005.
8. Soumyajit Saha and Debasis Chakraborty:“Numerical Exploration of Starting Process in Supersonic Nozzle” Aeronautical Journal ,  Vol  111 No.  1115, pp 51 - 58 January 2007.
9. P. Manna,Ramesh Behera, and Debasis Chakraborty “Design and Analysis of Liquid Fueled Strut Based Scramjet Combustor – A CFD Approach” AIAA Journal of Propulsion and Power Vol 24, No. 2. March – April, 2008, pp 274-281.
10. Debasis Chakraborty (2010) “CFD based design of kerosene fueled scramjet combustor”, InternationalJournal of Hypersonics, Vol 1, No 1, pp 14-29.
11. Malsur Dharavath, P. K. Sinha and Debasis Chakraborty(2010): “Simulation of Supersonic Base Flow – Effect of Computational Grid and Turbulence Model”,Proc. I Meche, Part G, Journal of Aerospace Engineering. Vol 224, No. 3, pp 311-319, 2010.
12. MSR Chandra Murty, M Sambasiva Rao and Debasis Chakraborty(2010) “Numerical Simulation of Nozzle Flow field with Jet Vane Thrust Vector Control”,   Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 224, No5, pp 541-548.
13. Aswin G and Debasis Chakraborty (2010): “Numerical Simulation of Transverse Side Jet Interaction with Supersonic Free Stream”, Aerospace Sciences and Technologies Journal. Vol 14, pp 295-301.
14. MSR Chandra Murty, R. D. Mishal and Debasis Chakraborty (2010): “Numerical Simulation of supersonic combustion with parallel injection of Hydrogen fuel”, Defence Science Journal. Vol 60, No 5, Sept 2010, pp 465-475.
15. DebasisChakraborty: “Forty years of CFD research in India – Achievements and Issues”, Guest editorial, Defence Science Journal, Vol 60, No. 6, pp 567-576,2010.
16. K.P. Singh, J. S. Mathur, V. Ashok and Debasis Chakraborty:  “CFD in Aerospace Industry in India” Defence Science Journal, Vol 60, No. 6, pp 639-652. 2010.
17. A.T. Sriram and Debasis Chakraborty “Numerical Simulation of staged transverse injection into Mach 2 flow behind a backward- facing step”,Defence Science Journal, Vol 61, No. 1, pp 3-10, 2011.
18. Vaibhav Shah, Rohit R. More, S. Srinivasa Raju, K. Anandhanarayanan R. Krishnamurthy and Debasis Chakraborty: “Estimation of Captive Flight Loads using Grid-free Euler Solver”, Journal of Aircraft, Vol 48, No.4, pp 1273-1279, July-August, 2011.
19. MSRChandra Murty and Debasis Chakraborty: “Effect of injection angle in mixing and combustion characteristics of scramjet combustor” International Journal of Hypersonics, Vol2, No.1-2, 2011, pp15-27.
20. S. Saha, S. Rathod, M. S. R Chandra Murty, P.K.Sinha and Debasis Chakraborty “Numerical simulation of base flow of a long range flight vehicle” Acta Astronautica , Vol 74, No. 3, pp 112-119, May-June, 2012.
21. Soumyajit Saha and Debasis Chakraborty: “Hypersonic Intake starting characteristics – A CFD Validation study”, Defence Science Journal, Vol 62, No. 3, May,2012, pp 147-152.
22. Rahul Ingle and Debasis Chakraborty:  “Numerical Simulation of Dual Mode Scramjet Combustor with significant upstream interaction”, International Journal of Manufacturing, Materials, and Mechanical Engineering, Vol 2, No. 3, July-September, 2012, pp 60-74.
23. MSR Chandra Murty and Debasis Chakraborty “Numerical Simulation of angular injection of Hydrogen fuel in scramjet combustor”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 226, 7 pp 861-872, July, 2012.
24. Javed, P. Manna and Debasis Chakraborty “Numerical Simulation of Dual pulse Rocket motor flow field” Defense Science Journal, Vol 62, No.6, Nov. 2012 pp 369-374.
25. Malsur Dharavath, P. Manna & Debasis Chakraborty: “Thermochemical exploration of Hydrogen Combustion in generic Scramjet Combustor”Aerospace Sciences and Technologies Journal., Vol 24, pp 264-274,2013..
26. Afroz Javed,Debasis Chakraborty and P.J. Paul “Model free simulation of compressible mixing layers”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 227(6), pp 977-991, 2013.
27. R. Balasubramanian, Vaibhav Shah, Konark Arora, R.Krishnamurthy and Debasis Chakraborty “Numerical Investigations of Lateral Characteristics of an Air-to-Air Missile”, AIAA Journal of Aircraft , Vol 50, No1, Jan 2013, pp 88-95.
28. P. Manna, Malsur Dharavath, P.K. Sinha and Debasis Chakraborty, “Optimization of a Flight worthy  scramjet Combustor through CFD”, Aerospace Science and Technologies, Vol 27, pp138-146, 2013.
29. S. Saha and Debasis Chakraborty: “Plume Ducting System Design of Vertical Launcher using CFD Tools”, Journal of Spacecraft and Rockets, Vol 50, No. 3, May – June 2013, pp 715-718.
30. K. Anandhanarayanan, Konark Arora, Vaibhav Shah, R. Krishnamurthy and Debasis Chakraborty“Separation Dynamics of Air-to-Air-Missile using a Grid-free Euler Solver”, AIAA Journal of Aircraft, Vol 50, No. 3, May – June 2013, pp 725-731.
31. Konark Arora,Vaibhav Shah,K Anandhanarayana,R Krishnamurthyand Debasis Chakraborty “Influence of aircraft flow field on the longitudinal stability of a missile”,  Defence Science Journal, Vol 63, No. 3, May 2013, pp 242-248.
32. MSR Chandra Murty, P. Manna and Debasis Chakraborty:”Conjugate Heat Transfer analysis in high speed flows”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 227, No. 10, pp 1672-1681, Oct-2013.
33. Malsur Dharavath and Debasis Chakraborty, “Numerical simulation of supersonic jet impingement on inclined plate, Defense Science Journal, Vol 63, N0.4, pp 355-362, July, 2013.
34. H S Mukunda, P. J Paul, Afroz Javed and Debasis Chakraborty, “Extension of the Universal erosive burning law to partly symmetric propellant grain geometries”, Acta Astronautica , Vol 93, pp 176-181, 2014.
35. Afroz Javed, NKS Rajan, and Debasis Chakraborty: “Effect of Side Confining Walls on the Growth Rate of Compressible Mixing Layers”, Computers and Fluids, Vol 86, pp 500-509, 2013..
36. Afroz javed, P K Sinha & Debasis Chakraborty, “Numerical Exploration of Solid Rocket Motor Blast Tube Flow Field”, Defense Science Journal Vol 63, No. 6, pp 616-621, November, 2013.
37. Afroz Javed  and Debasis Chakraborty, “Prediction of Solid Rocket Motor Nozzle Damping Coefficient using CFD Techniques ”, Journal of Propulsion and Power , Vol 30, issue 1, pp 19-24, 2014.
38. MSR Chandra Murty and Debasis Chakraborty: “Coupled external internal flow simulation of LFRJ vehicle”, Aerospace Science and Technologies, Vol 36, pp1-4, July, 2014.
39. Kalyana Chakravarthy and Debasis Chakraborty: “Modified SLAU2 scheme with advanced shock stability”, Computers and Fluids , Volume 100, pp 176-184, September 2014.
40. Malsur Dharavath, P. Manna & Debasis Chakraborty, “Numerical Investigation of Hydrogen Fuelled Scramjet Combustor with/without Cavity Flameholder”, Defence Science Journal, Vol 64, No. 5, pp 417-425, September, 2014.
41. Afroz Javed,P.J. Paul, NKS Rajan and Debasis Chakraborty “Exploration of supersonic confined Mixing Layer – Effect of dissimilar gases at different temperatures”,  Proc. I Meche, Part G, Journal of Aerospace Engineering Vol 228 (10), pp 2255-2265, October, 2014.
42. P. K. Sinha and Debasis Chakraborty” Numerical study of flow inside a tube during hot launching of rocket”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 228, pp2604-2611, December, 2014.
43. Afroz Javed, NKS Rajan and Debasis Chakraborty:”Behaviour of Turbulent Prandtl and Schmidt Numbers in a Compressible Mixing Layer”, Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 229 (7), June, 2015, pp 1349-1359. Doi: 10.1177/0954410014547441.
44. Amit Kumar Chaturvedi,  Sudarshan Kumar,  Debasis Chakraborty:  “Slag prediction in submerged rocket nozzle through two phase CFD simulation”, Defense Science Journal, Vol 65, No 2, March 2015, pp 99-106. DOI: 10.14429/dsj.65.7147.
45. Afroz Javed and Debasis Chakraborty: “Universal erosive burning model performance for solid rocket motor internal ballistics”, Aerospace Science and Technologies, Vol 45(2015), pp 150-153,http://dx.doi. org/10.1016/j.ast.2015.05.005.
46. Arvind Iyer, Afroz Javed and Debasis Chakraborty: “A new internal ballistic program for rocket motor performance prediction”, Defence science journal, Vol 65, No 3, May 2015, pp181-188. DOI:10.14429/ dsj.65.8304..
47. Soumyajit Saha and Debasis Chakraborty: “Numerical simulation hypersonic air intake”, Defence science journal,  Vol 65, No 3, May 2015, pp189-195. DOI:10.14429/dsj.65.8254.
48. Malsur Dharavath, P Manna and Debasis Chakraborty: “Numerical exploration of dissimilar supersonic coaxial jets mixing”,  Acta Astronautica, Vol 111, June-July 2015, pp 308-316.
49. Afroz Javed, NKS Rajan and Debasis Chakraborty “Compressible Mixing Layers: RANS Simulations with k-ε Turbulence Model” , Proc. I Meche, Part G, Journal of Aerospace Engineering, Vol 229(9), pp 1650-1660, 2015. Doi: 10.1177/0954410014548318.
50. Kalyana Chakravarthy, Konark Arora and  Debasis Chakraborty:”A simple hybrid finite volume solver for compressible turbulence”, International Journal of Numerical Methods in Fluids, Vol 77, pp 707-731.
51. MSR Chandra Murthy and Debasis Chakraborty: “Numerical characterization of jet vane based thrust vector control systems”,  Defence science journal, Vol 65, No. 4, pp261-264, July,2015.
52. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Tip to tail simulation of a hypersonic airbreathing cruise vehicle”, Journal of Propulsion and Power , Vol 31(5), pp 1370-1379,  September –October, 2015, DOI:10.2514/1.B35686.
53. Malsur Dharavath, P. Manna and Debasis Chakraborty:“Study of mixing and combustion in scramjet combustor with ethylene fuel through CFD”, Acta Astronautica, Vol 117, pp 305-318, 2015.
54. MSR Chandra Murty, Anand V Bhandarkar and Debasis Chakraborty:”Aerothermal exploration of reaction control jet in supersonic crossflow at high altitude”, Aerospace Science and Technology, Vol 50(2016), pp 266-271 , DOI: 10.1016/j.ast.2016.01.004.
55. Malsur Dharavath, P. Manna, P.K. Sinha and Debasis Chakraborty “Numerical analysis of a kerosene fuelled scramjet combustor” ASME Journal of Thermal Science and Engineering Applications, Vol 8, issue 8, March 2016, pp. 0111003-1-7.  DOI:10.1115/1-4030699..
56. Soumyajit Saha and Debasis Chakraborty: “CFD simulation of combustion instability in solid rocket motor: implementation of pressure coupled response function”, Defense Science Journal, Vol 66, No. 3, May 2016, pp 216-221, DOI:10.14429/dsj/66.9058.
57. Anand Bhandarkar, Malsur Dharavath, MSR Chandra Murty, P. Manna and Debasis Chakraborty, ” A novel CFD method to estimate heat transfer coefficient for high speed flows” Defense Science Journal, Vol 66, No. 3, May 2016, pp 203-209, DOI:10.14429/dsj/66.8873.
58. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Numerical simulation of tip-to-tail for a hypersonic test vehicle with ethylene fuel”, Acta Astronautica (128), pp 107-118, 2016,  DOI: 10.1016/ j.actaastro.2016.07.014.
59. V. Kalyana Chakravarthy, Arvind Iyer and Debasis Chakraborty: “Quasi-one-dimensional modelling of internal ballistics and axial acoustic oscillations in solid rocket motors”, Jl of Propulsion and Power, Vol 32(4), pp 882-891, DOI: 10.2514/1.B35754.
60. K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Validation of a grid free viscous solver for a hypersonic configuration”, AIAA Journal, Vol 54, No.10, Oct-2016, pp3310-3313 DOI:10.2514 /1.J054863).
61. R. Balasubramanian, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty:”Magneto-hydrodynamic flow control of a hypersonic cruise vehicle based on AJAX concept using CERANS-MHD”, Journal of Spacecraft and Rockets, Vol 53(4), pp 759-762,  DOI:10.2514/1. A33573).
62. Anand Bhandarkar, Souraseni Basu, P. Manna and Debasis Chakraborty: “Aerodynamic characteri-zation of ramjet missile through combined external-internal CFD simulation”, Defense Science Journal, Vol 66, No.6, pp 624-629, November, 2016, DOI:10.14429/dsj.66.9677.
63. Anand Bhandarkar, P. Manna and Debasis Chakraborty: “Modeling of droplet breakup in high speed cross flow “,Atomization and Sprays, Vol 27, No. 1, pp 61-79, 2017.
64. Ankit Raj,K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Numerical simulation of ground test of fairing separation for hypersonic airbreathing vehicle”, Proc. IMechE, Part G: Journal of Aerospace Engineering, Vol 231(2), pp 319-325, (DOI:10.1177/0954410016636911.
65. Arvind Iyer, V.Kalyana Chakravarthy, Soumyajit Saha  and Debasis Chakraborty : “ Damping of model perturbation in solid rocket motor”, Aeronautical Journal, Vol 120, N0. 1231, pp 1425-1445, September 2016 (DOI: 10.1017/aer.2016.65).
66. M. Srinivas Rao, Afroz Javed and Debasis Chakraborty: “Numerical characterization of supersonic exhaust diffuser”, Defense Science Journal, Vol 67, No. 2, pp 219-223, March, 2017, DOI: DOI:10.14429 /dsj.67.9544.
67. MSR Chandramurthy, P.K. Sinha and Debasis Chakraborty: “Numerical simulation of missile motion in the canister: effect of rocket exhaust on adjoining launching system”, Proc. IMechE Part G,Journal of Aerospace Engineering, Vol 231(11), pp 2085-2097,DOI: 10.1177/0954410016662064.
68. Afroz Javed and Debasis Chakraborty:” Evaluation of Side Spillage for a Hypersonic Air Intake using CFD Techniques” Proc. IMechE Part G,Journal of Aerospace Engineering, Vol 231(11), pp 2111-2119, DOI:10.1177/0954410016660873.)
69. V. Kalyana Chakravarthy and Debasis Chakraborty:“Damping numerical oscillations in hybrid solvers through detection of Gibbs phenomenon”, International Journal in Numerical methods in Fluids, Vol 84, pp 699-714,  (Online version published on 10th March, 2017), DOI: 10.1002/fld.4367.
70. Kalyan Chakravarthy, Debasis Chakraborty:  “Vortex pairing and reverse cascade in simulated two dimensional rocket motor like flow field”,Physics of Fluids, Vol 29, 075104(2017), DOI:10.1063/1.4989420.
71. Souraseni Basu, Soumyajit Sahaand Debasis Chakraborty: “Numerical simulation of missile jet deflector”, AIAA journal of spacecraft and rockets, Vol 54, No. 4, July-August, 2017, pp1-6, DOI: 10.2514 / 1.A33761.
72. Kalyana Chakravarthy, Konark Arora, Debasis Chakraborty: “LES of  flows past backward facing step using digitally filtered inflow conditions”, European Journal of Fluid Mechanics/B. Fluids, Vol. 67, pp 404-416.
73. K. Anandhanarayanan, R. Krishnamurthy and  Debasis Chakraborty: “Store Separation Studies for an AAM and validation with Flight Data”,  Defence Science Journal, Vol 68, No.1, January 2018, pp 5-11, DOI: 10.14429/dsj.68.11480.
74. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Mixing studies of slot injection in supersonic flows” Defence Science Journal, Vol 68, No.2, March 2018, pp 121-128, DOI: 10.14429/dsj.68.11069.
75. Konark Arora, Kalyan Chakravarthy and Debasis Chakraborty:”Large Eddy Simulation of Supersonic, Compressible, Turbulent Mixing Layers”, Aerospace Science and Technology,  Vol 86, pp 592-598, 2019.
76. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Effect of Location of a Transverse Sonic Jet on Shock Augmented Mixing in a SCRAMJET Engine”, Aerospace Science and Technology, 96 (2020), 105535.
77. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Determination of Optimal Spacing between Transverse Jets in a SCRAMJET Engine”, Aerospace Science and Technology, 96 (2020), 105520.
78. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Computational analysis of transverse sonic injection in supersonic cross flow using RANS models”, ASME Journal of Fluid Engineering, 2019.
79. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Effect of fuel-Jet Injection on shock augmented air-fuel Mixing and overall performance of a SCRAMJET Engine”, Aerospace Science and Technology. 100 (2020) 105786,
80. K.Anandhanrayanan, Ankit Raj, R. Krishnamurthy and Debasis Chakraborty: “Engineering method of prediction of plume path of air launched missile”, Defence Science Journal, Vol. 70, No. 2, March 2020, pp. 201-206, DOI : 10.14429/dsj.70.13853.

A2. Refereed National Journal Publication

1. A.P. Roychowdhury and Debasis Chakraborty: “Review of Supersonic Boundary Layer Instability and Transition Models”, Indian Journal of Radio and Space Physics, Vol. 29, pp 273 - 284, October 2000.
2. Debasis Chakraborty, Pradeep Kumar, R. Balu and V. Adimurthy: “Numerical Simulation of Axisymmetric Base Flow in the Presence of Propulsive Jet”, Journal of Aerospace Sciences and Technologies, Vol 53 No. 1, pp 35 – 38, Feb-March 2001.
3. P. Manna and Debasis Chakraborty: “Numerical Investigation of Conjugate Heat Transfer Problems” Journal of Aerospace Sciences and Technologies, Vol 56 No. 3, pp 166– 175, August 2004.
4. P. Manna  and  Debasis Chakraborty: “Numerical Simulation of Transverse H2 Combustion in Supersonic Airstream in a Constant Area Duct” Journal of Institute of Engineers, Vol 86, November, 2005, pp 47-53.
5. Afroz Javed and Debasis Chakraborty : “Numerical simulation of supersonic combustion of pylon injected hydrogen fuel in scramjet combustor”Journal of Institute of Engineers Vol 87, May, 2006, pp 1-6. (Awarded the Aerospace Engineering Division Prize of Institution of Engineers (India) for 2006-2007).
6. Ramesh Behera and Debasis Chakraborty:“Numerical simulation of Kerosene Fueled Ramp Cavity Based Scramjet Combustor”Journal of Aerospace Sciences and Technologies, Vol 58, No. 2, May 2006, pp 104 – 111.
7. P. Manna, Ramesh Behera and Debasis Chakraborty: “Thermochemical exploration of a cavity based supersonic combustor with liquid kerosene fuel” Journal of “Aerospace Sciences and Technologies” Vol 59, No 4 pp 246-258, Nov, 2007.
8. P. Manna and Debasis Chakraborty “Numerical Investigation of Confinement Effect on Supersonic Turbulent Flow Past Backward Facing Step with and without Transverse Injection”  Journal of Aerospace Sciences and Technologies, Vol 61, No.2 , pp283-294, May, 2009.
9. P. Manna, Malsur Dharavath and Debasis Chakraborty “Performance Improvement of Kerosene Fuelled Scramjet Combustor Through Modified Fuel Injection – A CFD Study”, Journal of Aerospace Sciences and Technologies ,Vol 61, No.2,pp 496-503, 2009.
10. Soumyajit Saha, P.K. Sinha and Debasis Chakraborty:  “CFD Prediction of Ramjet Intake Characteristics at Angle of Attack”, Journal of Aerospace Sciences and Technologies , Vol 62, No. 3, pp159-165, August 2010.
11. Soumyajit Sahaand Debasis Chakraborty “Reacting flow computation of staged supersonic combustor with strut injection”,Journal of Aerospace Sciences and Technologies, Vol 63, No.4 , Nov, 2011, pp289-298.
12. R. Balasubramanian, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Numerical Simulation of Stage Jettisoning of a Two-Stage Rocket with Different Separation Distances”, Journal of Institute of Engineers (Series C) C, Vol 93 , Issue 4, pp 345-350,Oct-Dec 2012.
13. Malsur Dharavath and Debasis Chakraborty: “Numerical simulation of underexpanded sonic jet”, Journal of Aerospace Sciences and Technologies.Vol 64, No.4, pp 259-267.
14. S.Saha, P.K.Sinha and Debasis Chakraborty “Numerical Prediction of surface heat flux during multiple jets firing for missile control”, Journal of Institute of Engineers (India) Series C, Vol 94, Issue 1, pp 85-91,January, 2013.
15. Malsur Dharavath, P. Manna and Debasis Chakraborty:“Effect of turbulence models and spray parameters on kerosene fuelled scramjet combustor” Journal of Aerospace Science and Technology, Vol 67 , No. 3, pp 369-383, August, 2015.
16. R. Balasubramanian, Jessy Prabhu Dayal, R. Krishnamurthy and Debasis Chakraborty: “Aero-propulsive Characterization of a Flight Vehicle with two side-jets using CERANS”, Journal of Aerospace Sciences and Technologies, Vol 68, No. 1, pp 8-16, February 2016.
17. Malsur Dharavath, P. Manna and Debasis Chakraborty, “Numerical exploration of low altitude rocket plume in aircraft vicinity”, Journal of Aerospace Sciences and Technologies, Vol 68, No. 4, pp 221-232.
18. Anand Bhandarkar, Malsur Dhravath, P. Manna and Debasis Chakraborty:”Conjugate Heat Transfer analysis in scramjet combustor”, Journal of Aerospace Sciences and Technologies, Vol 68, No. 4, pp 266-275.
19. Soumyajit Saha and Debasis Chakraborty: “Role of viscosity in hypersonic intake starting phenomenon”, Journal of Aerospace Sciences and Technologies, Vol 69, No. 1, pp18-24, February, 2017.
20. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Numerical Simulations of non equilibrium plasma discharge for flow control of aerospace vehicles”, Journal of Institute of Engineers (series ‘C’), Vol 98, issue 3, June 2017, pp 285-293, DOI: 10.1007/ S40032- 016-0314-1) (Selected as subject prize).
21. MSR Chandra Murty and Debasis Chakraborty: “Plume interaction and base flow analysis of a twin engine flight vehicle”, Journal of Institute of Engineers (Series ‘C’) Vol 98, issue 3, June 2017, pp 379-385, DOI: 10.1007/S40032-016-0296-z.
22. Malsur Dharavath, P. Manna and Debasis Chakraborty, “Numerical simulation of hydrogen air supersonic coaxial jet”, Journal of Institute of Engineers (Series ‘C’) Vol 98, issue 5, October 2017, pp 575-585,DOI: 10.1007/S40032-016-0291-4.
23. Afroz Javed and Debasis Chakraborty: “Numerical Simulations of canted nozzle and scarfed  nozzle Flow Field”, Journal of Institute of Engineers (Series ‘C’) Vol 98, issue 5, October 2017, pp 625-633, DOI: 10.1007 / S40032-016-0305-z).
24. Afroz Javed, Debasis Chakraborty: “Numerical Simulations of Static Tested Ramjet Dump Combustor”, Journal of Institute of Engineers, Series’C (special issue on “Aerothermodynamics of Aerospace Propulsion), Vol 97, Issue 3, June 2016, pp 1-9,  DOI: 10.1007 / S40032-016-0312-z).
25. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Mitigation of shock induced flow separation using Magnetohydrodynamics flow control”, SADHANA , Vol 42, Issue 3, March, 2017, pp 379-390, DOI: 10.1007/s12046-017-0610-3).
26. PVRR Bhogendra Rao, K Ananadhanarayanan, R Krishnamurthy and Debasis Chakraborty  “CUDA computation of a Grid-free Solver”,Journal of Aerospace Sciences and Technologies, Vol. 70, no.2, pp 111-119, May, 2018.
27. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Prediction of heat flux in a scramjet combustor with kerosene fuel through CFD”, Journal of Aerospace Sciences and Technologies, Vol. 70, no.2, pp 85-97, May, 2018.
28. R. Balasubramanian, K. Anandhanarayanan R Krishnamurthy and Debasis Chakraborty: “Transport equation transition modeling in CERANS for hypersonic flow”, Journal of Aerospace Sciences and Technologies, Vol 70, No.4, pp 358-371.
29. Anand Bhandarkar, MSR Chandra Murty and Debasis Chakraborty:“CFD driven aero-propulsive design of ramjet vehicle”, Journal of Aerospace Science and Technology, Vol. 71, No.3, August, 2019,pp 281-188.
30. PVRR Bhogendra Rao, K Ananadhanarayanan, R Krishnamurthy and Debasis Chakraborty: “MPI-CUDA Implementation of Implicit Euler Flow Solver in Grid-free Framework”, Journal of Aerospace Science and Technology, Vol. 71, No.3, August, 2019, pp 301-306.

A3 Paper under Review/Preparation

1. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Magneto-hydrodynamics flow control for heat flux mitigation and aerobraking of hypersonic blunt body flow field”, Paper under review in Defence Science Journal.
2. Kalyan Chakravarthy and Debasis Chakraborty:”Contribution of pressure coupled propellant response tolinear stability of solid rocket motors”, Paper communicated to Journal of Sound and Vibrations.
3. MSR Chandra Murty, Joseph Mathew and Debasis Chakraborty: “Thermal behavior of a dual mode Scramjet; wall heat transfereffects on thermal choking and mean flow gas dynamics”, Paper being communicated to Physics of Fluids.
4. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Effect of fuel-Jet Injection on shock augmented air-fuel Mixing and overall performance of a SCRAMJET Engine”, Paper under review in Aerospace Science and Technology.
5. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “High speed missile control using transverse sonic jet injectors: A validation study”, Paper communicated to Aerospace Science and Technology.
6. Vatsalya Sharma, Vinayak Eswaran and Debasis Chakraborty: “Influence of the Isolator Section length on the Performance of a SCRAMJET Engine”, Paper under review in Shock waves.

B Book Chapters

1. Debasis Chakraborty (2008): “Numerical Simulation of Liquid Fueled SCRAMJET Combustor Flow Field”, in Current Trends in Engineering Practice”, Vol II,  pp 449-464, Edited by Sneh Anand, Narosa Publishing House, New Delhi, 2010.
2. Debasis Chakraborty (2008): “Development and application of CFD Technique in Aero-propulsive characterization of missiles”, Current Trends in Engineering Practice, Vol II,  pp 432-448, Edited by Sneh Anand, Narosa Publishing House, New Delhi, 2010.
3. Arvind Iyer, NKS Rajan and Debasis Chakraborty: “Evolution of URANS Model of High Speed Mixing Layers usingLES”, Advances in Computational, modeling and control of transitional and turbulent flows, pp 137-145, World Scientific Publishing Company, 2016.
4. V. Kalyana Chakravarthy and D. Chakraborty: “Damping numerical oscillations in hybrid solvers through detection of Gibbs phenomenon”, Advances in Computational, modeling and control of transitional and turbulent flows, pp 406-415, World Scientific Publishing Company, 2016.
5. Debasis Chakraborty (2018):“CFD methods in high speed air-breathing missile propulsion design”, Book chapter in “Innovations in Sustainable Energy and Cleaner environment” (Green Energy and Technology series) , edited by  Ashwin K Gupta, Ashoke De, Suresh K Agarwal, Abhijit Khusari and Akshai Runchal, pp 263-292, ISSN: 1865-3529, DOI: 10.1007/978-981-13-9012-8. Proceedings of  International Workshop on Sustainable Energy, Power and Propulsion (ISEPP-2018), March 18-22, 2018, National Institute of Technology, Kurukshetra, Harayna.

C1. Published Proceedings of International Conferences

1. Debasis Chakraborty: “Evaluation of empirical combustion models for high speed H2 – Air confined mixing layer using DNS data” Proceedings of international workshop on modern advances in combustion at Indian Institute of Technology, Madras, during August 31 – September 1, 2001.
2. P. J. Paul, Debasis Chakraborty and H.S. Mukunda (2001): “An exploration of supersonic mixing layers”, Proceedings of International Workshop on Modern Advances in  Combustion, Indian Institute of Technology, Madras, August 31 – September 1, 2001 (Invited lecture).
3. Debasis Chakraborty, H S Mukunda and P J Paul (2002): “Direct Numerical Simulation of Confined Reacting Supersonic Mixing Layer”, Proceedings of the International workshop on turbulent reacting flows, IIT, Madras, December 19 – 20, 2002, pp 171 – 184.
4. Debasis Chakraborty, P. J. Paul and H. S. Mukunda (2003) : “Effect of stream temperature on the growth and structure of the supersonic mixing layers”, AIAA paper No. 2003 – 1205, 41st AIAA aerospace science meeting and exhibit, Reno, Nevada, Jan 6 – 9, 2003.
5. S. Saha, P.K.Sinha, S. Kumar, A.Satyanarayan and Debasis Chakraborty (2005): “Jet vane flowfield characteristics using CFD”, Recent trends in Aerospace Design and Optimization, Proceedings of SAROD-2005. pp 335-346.
6. P. Manna and Debasis Chakraborty “Numerical simulation of supersonic flow behind a backward facing step in free and confined environment”, AIAA paper No. 2005 – 3647, 41st AIAA/ASME /SAE /ASEE Joint Propulsion Conference, Arizona, USA , July 10 – 13, 2005.
7. Rahul Ingle and Debasis Chakraborty (2006) :  “Numerical Simulation of Dual Mode Scramjet Combustor with significant upstream interaction”, Paper No. AIAA – 2006- 7914, 14thAIAA / AIH Space plane and Hypersonic Conference, Cannebera, Australia, November 2006.
8. Soumyajit Sahaand Debasis Chakraborty (2006) “Reacting flow computation of staged supersonic combustor with strut injection”, AIAA Paper No. 2006-3895. 36th AIAA Fluid Dynamics Conference, San Francisco, USA, June 2006
9. P.K. Sinha, R. Krishnamurthy and Debasis Chakraborty (2007): “CFD in Aero propulsive design of missiles”, Proceedings of 7th Asian Computational Fluid Dynamics Conference (ACFD-7) held at Bangalore November 26-30, 2007. pp 68-83(Invited Lecture).
10. Vaibhav Shah, R. Balasubramanian, R. Krishnamurthy and Debasis Chakraborty (2007), “Numerical analysis of Launcher-Plume Jet-Deflector flow” Proceedings of SAROD-2007 held at Thiruvananthapuram,  November 22-23, 2007, pp 545-548
11. Debasis Chakraborty (2007): “Role of CFD in Aero-propulsive Characterization of missiles in DRDL”, Proceedings of SAROD-2007 held at Thiruvananthapuram , November 22-23, 2007. pp 23-40
12. K. Anandhanarayanan, Vaibhav Shah, R. Krishnamurthy and Debasis Chakraborty (2007) “Numerical Exploration of an Aerospace Vehicle with deflected fins using a grid-free solver”, Proceedings of SAROD-2007 held at Thiruvananthapuram  November 22-23, 2007. pp536-544.
13. P.B.Manna, Malsur Dharavath and Debasis Chakraborty (2007):  “ Numerical optimisation Study of Scramjet Combustor performance “, Proceedings of  International conference on High Speed Air and Space Transportation System held at Hyderabad during 29-30 June, 2007, pp 319-329.
14. A. Javed, P.K.Sinha and Debasis Chakraborty (2008) “Numerical Study of Underexpanded Jet”, NAL50:INCAST-International Conference on Aerospace Science and Technology Paper No INCAST-2008-P035
15. Rahul Ingle, P.K.Sinha and Debasis Chakraborty (2008) “Simulation of Transverse Injection in a Supersonic Stream”, NAL50:INCAST-International Conference on Aerospace Science and Technolgy Paper No. INCAST-2008-120
16. A.T. Sriram and Debasis Chakraborty (2008) “ Numerical Simulation of staged transverse injection into Mach 2 flow behind a backward- facing step”, NAL50:INCAST-International Conference on Aerospace Science and Technolgy”, Paper No. INCAST-2008-119
17. P. Manna and Debasis Chakraborty (2009): “Thermochemical exploration of Liquid  Fueled  Scramjet Combustor”, 7th Asia –pacific combustion conference.(Aspacc-09), Paper No. ID 10176
18. Debasis Chakraborty (2009) “CFD based design of kerosene fueled SCRAMJET combustor”, Proccedings of IISc Centenary International Conference and Exhibition on Aerospace Engineering (ICEAE2009), pp 377-386.
19. R. Balasubramanian, K. Anandhanarayanan, Vaibhav Shah,R. Krishnamurthy and Debasis Chakraborty (2009): “Surface Temperature Prediction for Flight Vehicle using CERANS” Science, Technologies and industry practice in Aerodynamics and Design. Proceedings of SAROD-2009, pp 454 - 462 Bangalore December10-12, 2009
20. MSR Chandra Murty and Debasis Chakraborty (2009) “Thermal response analysis of scramjet combustor wall to high speed turbulent reacting flow”, Science, Technologies and industry practice in Aerodynamics and Design. Proceedings of SAROD-2009, pp 698 – 710, Bangalore December10-12, 2009
21. MSR Chandra Murty and Debasis Chakraborty, “Numerical Simulation of angular injection of Hydrogen fuel in scramjet combustor”,Proceedings of 8th Asia –pacific conference on combustion (Aspacc-10), held at Hyderabad, India on Dec 10-13, 2010, pp 458- 465.
22. Malsur Dharavath, P. Manna & Debasis Chakraborty: “Thermochemical exploration of Hydrogen Combustion in generic Scramjet Combustor”Proceedings of 8th Asia –pacific conference on combustion (Aspacc-10), held at Hyderabad, India on Dec 10-13, 2010, pp 474- 481.
23. Debasis Chakraborty: “Design and Analysis of Missile Systems through CFD Simulations”, Proceedings of International Conference on Modeling, Optimization and Computing (ICMOC-2010), pp 50-58, NIT, Durgapur, October 28-30, 2010.
24. R. Balasubramanian, Vaibhav Shah, Konark Arora, R.Krishnamurthy and Debasis Chakraborty “Numerical Investigations of Lateral Characteristics of an Air-to-Air Missile”, Proceedings of Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011) November 16-18, 2011, Bangalore, India, Paper No.059-G04. pp 439-446.
25. Konark Arora, K. Anandhanarayanan,R. Krishnamurthyand Debasis Chakraborty: “Influence of aircraft flow field on the longitudinal stability of a missile” Proceedings of Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011) November 16-18, 2011, Bangalore, India, Paper No.060-G04. pp 447-451.
26. MSR Chandra Murty and Debasis Chakraborty: “Effect of injection angle in mixing and combustion characteristics of scramjet combustor” Proceedings of Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011) November 16-18, 2011, Bangalore, India, Paper No.041-G10. pp 808-818.
27. Malsur Dharavath and Debasis Chakraborty: “Numerical simulation of underexpanded sonic jet”, Proceedings of Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011) November 16-18, 2011, Bangalore, India, Paper No.040-G04. pp 406-413.
28. S. Saha, P.K.Sinha and Debasis Chakraborty: “Hypersonic Intake Starting characteristics – A CFD validation study”,  Proceedings of Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011) November 16-18, 2011, Bangalore, India, Paper No.009-G04. pp 376-380.
29. P. K. Sinha and Debasis Chakraborty” Numerical study of flow inside a tube during hot launching of rocket”, Proceedings of 4th International Congress on Computational Mechanics and Simulation held in IIT Hyderabad, 9-12 Dec, 2012.
30. Debasis Chakraborty”  CFD Methods in Aerodynamic and Propulsion Design of Missile”, Proceedings of 4th International Congress on Computational Mechanics and Simulation,  IIT Hyderabad, 9-12 Dec, 2012 (Invited Lecture).
31. Anand Bhandarkar, P.B. Manna,  P. K. Sinha and Debasis Chakraborty” Development of Engineering Method for prediction of Transient Temperature Rise of a surface exposed to plume of a moving missile”, Proceedings of the 22nd National and 11thInternational ISHMT-ASME Heat and Mass Transfer Conference, December 28-31, 2013, IIT Kharagpur, India, Paper No. HMTC1300599.
32. Malsur Dhravath, P.B. Manna,  P. K. Sinha and Debasis Chakraborty: Numerical analysis of a kerosene fuelled scramjet combustor”, Proceedings of the 22ndNational and 11thInternational ISHMT-ASME Heat and Mass Transfer Conference, December 28-31, 2013, IIT Kharagpur, India, Paper No. HMTC1300600.
33. Ankit Raj, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty:” Fairing Separation studies for hypersonic Technology Demonstrator Vehicle”Proceedings of  symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2013) held at Hyderabad during November 21-23, 2013, pp 150-156.
34. R. Balasubramanian, Jessy Prabhu Dayal, R. Krishnamurthy and Debasis Chakraborty: “Aero-propulsive Characterization of an Airborne Vehicle with Two Side-Jets using CERANS”Proceedings of  Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2013) held at Hyderabad during November 21-23, 2013, pp 444-449.
35. MSR Chandra Murty and Debasis Chakraborty: “Coupled external internal flow simulation of LFRJ vehicle”,  Proceedings of  Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2013) held at Hyderabad during November 21-23, 2013, pp 650-655.
36. Arvind Iyer, NKS Rajan and Debasis Chakraborty: “Evolution of URANS Model of High Speed Mixing Layers usingLES”, Proceedings of IUTAM Symposium on Advances in Computation, Modeling and control of Transitional and turbulent flows, December 15-18,2014 Goa, India(Paper No. 66).
37. V. Kalyana Chakravarthy and D. Chakraborty: “Damping numerical oscillations in hybrid solvers through detection of Gibbs phenomenon”,Proceedings of Presented in IUTAM Symposium on Advances in Computation, Modeling and control of Transitional and turbulent flows, December 15-18,2014 Goa, India.(Paper No.68).
38. Anand Bhandarkar, Souraseni Basu, P. Manna and Debasis Chakraborty: “Combined external-internal flow simulation of a twin intake air-breathing missile configuration”, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, paper No.CP- 37,pp 137-140
39. M. Srinivas Rao, Afroz Javed and Debasis Chakraborty: “Numerical characterization of supersonic exhaust diffuser”, Proceedings  of7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, paper No.CP- 38, pp141-144.
40. Anand Bhandarkar, MSR Chandra Murty, P. Manna and Debasis Chakraborty:“CFD driven aero-propulsive configuration of an advanced solid fuel ducted ramjet based air breathing missile”, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, Paper No. CP-39, pp 145-149.
41. Malsur Dharavath, P. Manna and Debasis Chakraborty:“Numerical simulation Hypersonic Air Intake Performance at different angles of attack”, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) to be held at Thiruvananthapuram during December 3-5, 2015, Paper No. CP-40,  pp150-154.
42. Konark Arora, Kalyan Chakravarthy, Debasis Chakraborty:”Large Eddy Simulation of Supersonic, Compressible, Turbulent Mixing Layers, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, Paper No. CP-41, 155-162.
43. Ankit Raj, Vaibhav Shah, K.Anandhanarayanan R. Krishnamurthy and Debasis Chakraborty: Separation studies of air to air missile from fighter aircraft using grid free solver”, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, paper No. CP-51, pp 178-183.
44. K.Anandhanarayanan, Ankit Raj, R. Krishnamurthy and Debasis Chakraborty: “Novel Aero-grid method for store separation Dynamics”, Proceedings of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, paper No. CP-52, pp184-188.
45. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Mitigation of shock induced flow separation using Magnetohydrodynamics flow control”, Proceedings  of  7thSymposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015) held at Thiruvananthapuram during December 3-5, 2015, Paper No. CP-53, pp189-196.
46. Souraseni Basu, P. Manna and Debasis Chakraborty: “Analysis and reduction of reaction mechanism for hydrocarbon combustion”, Proceedings of  10th International High Energy Materials Conference and Exhibits, Feb 11-3, 2016, Hyderabad, pp 393-397.
47. MSR Chandra Murthy and Debasis Chakraborty: “ Numerical simulation of canister transient flow  field: Effect of jet deflector  geometry”,  Proceedings of  10th International  High Energy Materials Conference and Exhibits, Feb 11-3, 2016, Hyderabad, pp 593-597.
48. Kalyan Chakravarthy and Debasis Chakraborty: “Numericalsimulation of transition to turbulence in solid rocket motor using LES” , Proceedings of  10th International High Energy Materials Conference and Exhibits, Feb 11-3, 2016, Hyderabad, pp 538-542.
49. Anand Bhandarkar, MSR Chandra Murty, P. Manna and Debasis Chakraborty:”Numerical Investi-gation of Underwater Supersonic Gaseous Jet:, Proceedings of the 6th International and 43rd National Conference on Fluid Mechanics and Fluid Power, December 15-17, 2016, MNNITA, Allahabad, U.P., India, Paper No. FMFP 2016-171
50. Debasis Chakraborty: “Development and Applications of CFD Techniques in Aero-propulsive Design of Missiles”, Proceedings of the 6th International and 43rd National Conference on Fluid Mechanics and Fluid Power, December 15-17, 2016, MNNITA, Allahabad, U.P., India, Paper No. FMFP 2016-TH-06(Invited Lecture)
51. Nagendra Kumar, P.A. Ramakrishna,Kalyan Chakravarthy, Debasis Chakraborty:“Computational studies on erosive burning of solid rocket motor with propellant combustion, Digital proccedings of 8th  European Combustion meeting,18-21 April 2017, Dubrovnik, Croatia.
52. Malsur Dharavath, P. Manna, Debasis Chakraborty:”Effect of fuel injection on scramjet combustor performance with ethylene fuel”, Paper accepted in  24thNational and 2nd International ISHMT-ASTFE Heat and Mass Transfer Conference (IHMTC-2017), held at Hyderabad during 27-30 December 2017.
53. PVRR Bhogendra Rao, K Ananadhanarayanan, R Krishnamurthy and Debasis Chakraborty:   “Master-Slave Architecture Pattern for High Performance Computing with CUDA”, Proceedings of International conference on innovative technologies in Engineering (ICITE-2018), April 11-13, 2018, Hyderabad.
54. Debasis Chakraborty: “Role of High performance computing in engineering design” Proceedings of Second International Conference on Recent Innovations in Engineering and Technology, Hotel Marriott, Hyderabad, December 21 -22, 2017, ISBN:978-93-86647-85-6.
55. Debasis Chakraborty and Kalyan V Chakravarthy: “Towards modeling of combustion dynamics in solid rocket motors” Proceedings of Fifth International Conference on Computational Methods for Thermal problems (THERMOCOMP 2018) held at Indian Institute of Science, Bangalore during July 9-11, 2018.
56. Vatsalya Sharma, Debasis Chakraborty and Vinayak Eswaran: “Computational study of sonic injection in supersonic cross flow” (FMFP2018 - PAPER NO.110),Proceedings of 7th International and 45th National Conference on Fluid Mechanics and Fluid Power, held at IIT Bombay during December 10-12, 2018.
57. Ankit Raj, Srinivasaraju Sarikonda, R. Balasubramanian, K.Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Stage separation studies using CFD”, Proceedings of8thSymposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD-2018) organized at Bangalore during November 29-December 01, 2018.
58. MSR Chandra Murty, Joseph Mathew and Debasis Chakraborty: “Numerical Investigation of Hyshot-2 Dual Mode Scramjet Combustor Flow Field with Emphasis on Thermal Chocking” Paper accepted for oral presentation in 7th International and 45th National Conference on Fluid Mechanics and Fluid Power, to be held at IIT Bomaby during December 10-12, 2018.

C2.Published Proceedings of National Conferences

1. Debasis Chakraborty and S.K.Saxena (1991): “Finite volume computation of supersonic viscous flow”, Proceedings of 32nd congress of Indian Society of Theoretical and Applied Mechanics, IIT, Bombay, pp 125 - 141, 1991.
2. Debasis Chakraborty (1991): “Finite volume computation on supersonic inviscid axisymmetric flow In air intake and propulsive nozzles", Aerothermodynamics of Internal Flows, pp 103-113 Tata McGraw Hill, Bombay, India, Proceedings 6th National Convention of Aerospace Engineers,at IIT, Bombay, January 24-25, 1991.
3. Debasis Chakraborty (1994): “Computation of inviscid supersonic flow in an air intake”, Proceeding of Workshop on Intake Aerodynamics at National Aerospace Laboratory, pp 113-133 Bangalore, India, 1994.
4. H.V.Nagraja Upadhaya, Debasis Chakraborty, P.J.Paul and H.S.Mukunda (1997): “Computational studies on 2D- mixing layers under hypervelocity conditions”, Proceedings of the XV National conference on I.C. Engines and Combustion), pp 693 - 700, Chennai, India, December 17-19,1997.
5. Debasis Chakraborty, Pradeep Kumar, R. Balu and V. Adimurthy: (1999), “Numerical simulation of axisymmetric base flow in the presence of propulsive jet”, Proceedings of National conference on aerodynamics, Thiruvananthapuram, June, 1999.
6. Mathew George, Lazar T Chitilappily, Debasis Chakraborty, P. J. Paul and H. S. Mukunda (2000) “Computational studies of the flow field in an Ejector Ram Jet Engine", Proceedings of national conference on Air Breathing Engines, pp 364 - 374, Hyderabad, December, 2000.
7. Debasis Chakraborty, Ajoy P Roychowdhury, V Ashok and Pradeep Kumar (2001): “Numerical investigation of staged transverse sonic injection in Mach 2 stream in confined environment”.  Proceedings of “Workshop on CFD”, pp93-105, Aerospace Engineering Department, IIT, Kharagpur, December 5 – 7, 2001.
8. Soumayit Saha and Debasis Chakraborty (2003): “Numerical simulation of Scramjet combustor flow field”, Proceedings of the 54th Annual General Meeting of Aeronautical Society of India (awarded the second best technical paper in the conference), January, 2003, Calcutta
9. Debasis Chakraborty, T K Ganesh Annavaradham, G Balu and S Panneerselvam (2003): “Numerical Simulation of the forebody flow field of a hypersonic air breathing research vehicle (HRV)”. Proceedings of 6th National Conference on Air breathing engines and Aerospace Propulsion, 2003
10. P Manna and Debasis Chakraborty (2003): “Numerical Simulation of Transverse Gaseous Injection in a Non-reacting Supersonic Combustor”, proceedings of 17th National Convention of Aerospace Engineers and National Seminar on Indian Aerospace Vehicles: Technical challenges, Nov 03 –05, 2003, BIT, Mesra, PP 146 – 156.
11. Sumit Soni and Debasis Chakraborty (2004): “Transverse liquid jet injection into a supersonic flow”, Proceedings of 7th National Conference on Air breathing engines and Aerospace Propulsion, Nov 5-7, 2004, IIT, Kanpur, pp 563-570
12. Debasis Chakraborty (2004): “Numerical simulation of high speed airbreathing propulsion system” Proceedings of 18th National conference of aerospace engineers,Nov 17-19, IIT, Kharagpur, pp 7-17
13. P. Manna and Debasis Chakraborty (2004) : “Numerical Simulation of Transverse H2 Combustion in Supersonic Airstream in a Constant Area Duct”, Proceedings of 18th  National conference of aerospace engineers, Nov 17-19, 2004, IIT, Kharagpur. pp 128-132
14. Afroz Javed and Debasis Chakraborty : “Numerical simulation of supersonic combustion of pylon injected hydrogen fuel in scramjet combustor”Proceedings of 18th  National conference of aerospace engineers, Nov 17-19, 2004, IIT, Kharagpur. pp 122-127
15. Soumyajit Saha, P.K. Sinha and Debasis Chakraborty (2006):  “CFD Prediction of Ramjet Intake Characteristics at Angle of Attack”, Proceedings of 8th National Conference on Air breathing engines and Aerospace Propulsion, December 12-14, 2006, DIAT, Pune, pp 97-107.
16. Vaibav Shah, RR More, SS Raju, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty, “Estimation of captive flight loads of a flight vehicle using grid free Euler solver”, 12th Annual CFD Symposium, 11th-12th August, 2010, Bangalore
17. Debasis Chakraborty:“Recent Applications of CFD Techniques to Solve Complex Aeropropulsive Design problems of missiles”, Paper No. IP-1, pp 1-7, Proceedings of  13th Symposium of CFD Division of Aeronautical Society of India, August 11-12, 2011(Invited Lecture).
18. R. Balasubramanian, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Numerical simulation of stage jettisoning of a two-stage rocket with different separation distances”, Paper No. 149, 25th National Convention of Aerospace Engineers, BIT, Mesra Nov 4-5, 2011.
19. S.Saha, G. Aswin, P.K.Sinha and Debasis Chakraborty: “Numerical Prediction of surface heat flux during multiple jets firing for missile control” Paper No. 132, 25th National Convention of Aerospace Engineers, BIT, Mesra Nov 4-5-2011.
20. P. Manna,Malsur Dharavath, P.K. Sinha and Debasis Chakraborty:“Optimization of a Flight-worthy Scramjet Combustor through CFD”, 22nd National Conference on I.C. Engines and Combustion, (22nd NCICEC), NIT, Calicut, Dec 10-13, 2011.
21. Ch. Venkateswarlu, Konark Arora, K Anandhanarayanan,R Krishnamurthy and Debasis Chakraborty, “Determination of Captive Loads on camera pod  in presence of aircraft”, ”, Proceedings of 26th Convention of Aerospace Engineers, Hyderabad during 24-25th Nov, 2012., pp 32-35.
22. Afroz Javed  and Debasis Chakraborty, “Prediction of solid rocket motor nozzle damping coefficient using CFD techniques ”, Proceedings of 26th Convention of Aerospace Engineers, Hyderabad, 24-25th Nov, 2012., pp 150-154.
23. Kalyana Chakravarthy and Debasis Chakraborty, “Towards development of a LES solver for all flow speed”, Proceedings of 26th Convention of Aerospace Engineers, Hyderabad, 24-25th Nov, 2012., pp 162-166.
24. Malsur Dharavath, P. Manna and Debasis Chakraborty, “Numerical Exploration of a Cavity Based Supersonic Combustor with Hydrogen Fuel”, Proceedings of 26th Convention of Aerospace Engineers, Hyderabad during 24-25th Nov, 2012., pp 167-171.
25. R. Balasubramanian, S. Srinivasa Raju, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty, “A  high  fidelity  kinetic  heating  analysis  suite for  high  speed  flight vehicles”, Proceedings of 26th Convention of Aerospace Engineers, Hyderabad during 24-25th Nov, 2012, pp 198-202.
26. MSR Chandra Murty, Anand V. Bhandarkar, P. K. Sinha and Debasis Chakraborty:” Application of CFD based methods in the kinetic heating analysis of an Air-to-Air aerospace vehicle” , Proceedings of 26th Convention of Aerospace Engineers, Hyderabad during 24-25th Nov, 2012., pp 187-192.
27. Mrinal Mahoto, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Effect of Aerodynamic damping on store separation dynamics”, Paper No CP 18, Proceedings of 15th Annual CFD Symposium, 9-10 August, 2013, Bangalore.
28. K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Validation of a grid free Viscous solver for a hypersonic configuration”, Paper No CP 19, Proceedings of  15th Annual CFD Symposium, 9-10 August, 2013, Bangalore.
29. Srinivas Raju, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Separation study of store from weapon bay using grid free Euler solver”, Paper No. NCAE-02, Proceedings of 27th National Convention of Aerospace Engineers held at Dehradun on Nov 8-9, 2013.
30. Debasis Chakraborty: “CFD Methods in Aerodynamic and Propulsion Design of Missile” Compendium:  Platinum Jubilee celebration of Andhra Pradesh State Center of Institute of Engineers, pp 27-34, November 14, 2013
31. Mrinal Mahoto, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Prediction of aerodynamic loads on fairings of hypersonic vehicle”, Proceedings of  3rd National Symposium on Shock Waves, IIT, Bombay, February 21-23, 2014.
32. Ankit Raj, Mrinal Mahato, K.Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Fairing Separation Studies for Hypersonic Technology Demonstrator Vehicle” Paper no CP-01 Proceeding of 16th Annual CFD Symposium, 11-12 August, 2014, Bangalore.
33. MSR Chandra Murty and Debasis Chakraborty: “Numerical characterization of jet vane based thrust vector control systems”, paper no CP-02, proceeding of 16th Annual CFD Symposium, 11-12 August, 2014, Bangalore.
34. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Hypersonic Aerothermodynamics Simulation Toolkit”, Paper no CP-03, Proceeding of 16th Annual CFD Symposium, 11-12 August, 2014, Bangalore.
35. Malsur Dharavath, P. Manna and Debasis Chakraborty:“Effect of turbulence models on scramjet combustor performance with kerosene fuel”, Paper no  CP-04 Proceeding of 16th Annual CFD Symposium, 11-12 August, 2014, Bangalore.
36. Ankit Raj, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Store separation dynamics of an air to air missile with misalignments using grid free solver”, Paper no CP-13 Proceeding of 16th Annual CFD Symposium, 11-12 August, 2014, Bangalore.
37. Malsur Dharavath, P. Manna and Debasis Chakraborty:“Study of Mixing and Combustion in Scramjet Combustor with Ethylene Fuel through CFD”, Proceedings of  2nd National Propulsion Conference, IIT, Bombay, February 23-24, 2015(Paper No NPC-2015-21).
38. Afroz Javed, Debasis Chakraborty: “Numerical Simulations of Static Tested Ramjet Dump Combustor”, Proceedings of  2nd National Propulsion Conference, IIT, Bombay, February 23-24, 2015 (Paper No. NPC-2015-14).
39. Soumyajit Saha and Debasis Chakraborty: “Hypersonic Intake starting and unstarting phenomenon - A CFD validation study”, Proceedings of 2nd National Propulsion Conference, IIT, Bombay, February 23-24, 2015(Paper No. NPC-2015-18).
40. Arvind Iyer, Kalyana Chakravarthy and Debasis Chakraborty: “Estimation of damping phenomena in solid rocket motors”, Proceedings of  2nd National Propulsion Conference, IIT, Bombay, February 23-24, 2015(Paper No. NPC-2015-20).
41. Soumyajit Saha and Debasis Chakraborty: “CFD simulation of combustion instability in solid rocket motor: implementation of pressure coupled response function”, Proceedings of  2nd National Propulsion Conference IIT, Bombay February 23-24, 2015 (paper No. NPC-2015-26)
42. Debasis Chakraborty: Development and applications of CFD software for aerodynamic and propulsion design of missile, Annals of the Indian National Academy of Engineering, pp.67-77, Vol XII, April 2015.
43. Afroz Javed and Debasis Chakraborty: “Numerical Simulations of Canted Nozzle Flow Field”, Proceedings of 28th National Convention of Aerospace Engineers, Bangalore, 14-15 November, 2014.
44. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Numerical Simulations of non equilibrium plasma discharge for flow control of aerospace vehicles”, Proceedings of  28th National Convention of Aerospace Engineers, Bangalore,14-15 November, 2014.
45. Debasis Chakraborty:“Mathematical Modeling in Aerospace Vehicle design”Proceedings of All India Seminar on “Civilian Applications of Aerospace Technologies”, Institute of Engineers, Andhra Pradesh state Center, Visvesvaraya Bhawan, Hyderabad- 500004,pp 29-32, March 27-28, 2015.
46. Konark Arora, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Flow simulation around a helicopter”, Paper No- CP-16, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp72-75.
47.  K.Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Development of a preprocessor for grid-free solver”, Paper No- CP-29, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp 136-139.
48. Mrinal Mahato, Ankit Raj, K.Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Safe Separation of Fairing of  Hypersonic Technology Demonstrator Vehicle”, Paper No- CP-30, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp 140-143.
49. Anand Bhandarkar, Malsur Dharavath, P. Manna and Debasis Chakraborty: “Conjugate Heat Transfer  of Scramjet Combustor- A Validation Study”, Paper No- CP-31, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp 144-147.
50. V Kalyana Chakravarthy, Konark Arora and Debasis Chakraborty: “LES over backward facing steps flows using digitally filtered inflow conditions”, Paper No- CP-32, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp 148-151.
51. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Prediction of Heat Flux in a Scramjet Combustor with Kerosene Fuel through CFD”, Paper No- CP-37, Proceedings of 17th AESI-CFD Symposium, NAL, Bangalore, August 11-12, 2015, pp 168-177.
52. Malsur Dharavath, P. Manna and Debasis Chakraborty:  “Effect of free stream conditions on Scramjet Combustor Performance”,  Proceedings of  24th National Conference on I.C. Engines and Combustion (24th NCICEC-2015),  University of Petroleum and Energy studies, Dehradun, Uttarakhand, 30th Oct- 1st Nov, 2015, pp 247-251.
53. Malsur Dharavath, P. Manna and Debasis Chakraborty: “Improvement of a Hydrogen Fuelled Scramjet Combustor Performance through CFD”, Proceedings of 29th National Convention of Aerospace Engineers (29th NCAE), Institute of Engineers, Tamil Nadu State Center, Chennai, 17th – 18th Nov, 2015, Paper No. NCAS025.
54. K.Anandhanarayanan R. Krishnamurthy and Debasis Chakraborty: “Separation dynamics of launch vehicle fairings using aerodynamic grid method”, Proceedings of 29th National Convention of Aerospace Engineers (29th NCAE),  Institute of Engineers, Tamil Nadu State Center, Chennai, 17th – 18th Nov, 2015, Paper No. NCAS007.
55. R. Balasubramanian, K.Anandhanrayanan, R. Krishnamurthy and Debasis Chakraborty: “Magnetohydrodynamics flow control of a hypersonic cruise vehicle based on AJAX concept using CERANS-MHD”, Proceedings of  29th National Convention of Aerospace Engineers (29th NCAE), Institute of Engineers, Tamil Nadu State Center, Chennai, 17th – 18th Nov, 2015, Paper No. NCAS026.
56. Mrinal Mahoto, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: ”Fairing separation studies using CFD at ground test condition”, Proceedings of  18th  AESI-CFD Symposium, NAL, Bangalore, August 10-11, 2016, pp 1-4.
57. R. Balasubramanian, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty: “Aerobraking  of  reentry  flight  vehicle  using  Magnetohydrodynamics”,  Proceedings of  18th  AESI-CFD Symposium, NAL, Bangalore, August 10-11, 2016, pp 62-66.
58. Soumyajit Saha, Souraseni Basuand  Debasis Chakraborty: “Numerical simulation of missile jet deflector”  Proceedings of  18th  AESI-CFD Symposium  held at NAL, Bangalore, August 10-11, 2016, pp 67-70.
59. R. Balasubramanian, K. Anandhanarayanan, R. Krishnamurthy and Debasis Chakraborty:” Magneto- hydro dynamic flow control of hypersonic blunt body flowfield involving real gas effects”, Proceedings of  18th  AESI-CFD Symposium, NAL, Bangalore, August 10-11, 2016, pp 82-83.
60. Malsur Dharavath, P. Manna and Debasis Chakraborty : “Numerical Study on Mixing Phenomena in Supersonic Flows with Slot Injection”, Proceedings of  18th  AESI-CFD Symposium, NAL, Bangalore, August 10-11, 2016, pp 96-99.
61. Afroz Javed and Debasis Chakraborty:”Exhaust Jet Analysis during Booster Tail-off at Various Operating Temperatures”, Proceedings of  18th  AESI-CFD Symposium, NAL, Bangalore, August 10-11, 2016, pp 234-237.
62. S. Srinivasa Raju,R. Balasubramanian, R. Krishnamurthy and Debasis Chakraborty: “Airframe material selection for a hypersonic flight vehicle based on high fidelity aero thermal analysis”, Proceedings of30th National Convention of Aerospace Engineers, Institute of Engineers, Nov 25-26, 2016, Hosur, Tamil Nadu.
63. PVRR Bhogendra Rao, K Ananadhanarayanan, R Krishnamurthy and Debasis Chakraborty  “Grid-free Solver with CUDA Computing”, Paper No. CP-11, pp 42-45, Proceedings of 19th AESI-CFD Symposium  held at NAL, Bangalore, August 10-11, 2017.
64. Souraseni Basu, Soumyajit  Saha and Debasis Chakraborty:“Plume-canister interaction of a tube launched missile”, Paper  No - FMFP2017–141,44th National Conference on Fluid Mechanics and Fluid Power, held at Amrita University, Kollam, Kerala during December 14-16, 2017.
65. Malsur Dharavath, Rolex Ranjith, R.Monoj, P. Manna and Debasis Chakraborty:“Comparison of numerical and experimental skin temperature of a hydrocarbon fuelled scramjet combustor”, Paper No - FMFP2017–153,44th National Conference on Fluid Mechanics and Fluid Power, held at Amrita University, Kollam, Kerala during December 14-16, 2017.
66. Anand Bhandarkar, MSR Chandra Murty, P. Manna, AP Dash and Debasis Chakraborty:“Multi-phase flow numerical investigation of water spray cooled Rocket nozzle exhaust diffuser for altitude simulation”, Paper No - FMFP2017–155,44th National Conference on Fluid Mechanics and Fluid Power, held at Amrita University, Kollam, Kerala during December 14-16, 2017.
67. Debasis Chakraborty: “Development of Industry-standard CFD codes for Aerodynamic Design”Paper No - FMFP2017–155,44th National Conference on Fluid Mechanics and Fluid Power, held at Amrita University, Kollam, Kerala during December 14-16, 2017.
68. PVRR Bhogendra Rao, K Ananadhanarayanan, R Krishnamurthy and Debasis Chakraborty  “Master slave architecture for High Performance Computing  with CUDA”, Paper presented in International Conference on innovation in Engineering, 2018, April 11-13, 2018, Osmania University, Hyderabad, India.
69. R. Balasubramanian, K. Anandhanarayanan R Krishnamurthy and Debasis Chakraborty: “Transport equation transition modeling in CERANS for hypersonic flow”, (Paper No. CP-07),Proceedings of   20th AESI-CFD Symposium, pp 26-33,  held at NAL, Bangalore, August 10-11, 2018.
70. S. Mahesh, A. Maria Arockiam, R. Balasubramanian, R Krishnamurthy and Debasis Chakraborty: “ Computational analysis of a spinning projectile and evaluation of dynamic derivatives”, Proceedings of  32nd National Convention of Aerospace Engineers (NCAE 2018), pp 5-13, held at Birla Institute of Technology, Mesra during October 27-28, 2018.
71.  Debasis Chakraborty: “Computational Fluid Dynamics Techniques in Aeropropulsive Design of Missiles” Proceedings of two day national symposium on advances in aerospace materials and processes -2018 (AAMP-2018), pp 42-53, Department of Mechanical Engineering, Sreenidhi Institute of Science and Technology, Hyderabad, July 6-7, 2018.
72. MSR Chandra Murty, Joseph Mathew and Debasis Chakraborty, “Thermal behavior of a dual mode Scramjet; wall heat transfer effectson thermal choking and mean flow gas dynamics”, Paper submitted to Aerospace Research Students Symposium-2019 (AERES-2019) being organized by  Department of Aerospace Engineering, Indian Institute of Science, Bangalore during October 16-18,2019.