Heat transfer through MLI is a combination of solid conduction, radiation and, under atmospheric conditions, gaseous conduction. All of these forms are minimized in different ways. Interposing as many enclosing reflective surfaces (metallized sheets) as is practically possible between the object being insulated and its surroundings minimizes radiative heat transfer. One can minimize solid conduction heat transfer by minimizing the density of the low-conductance spacers between the reflective surfaces and making the blanket "fluffy" in order to minimize contact between layers. <ref name = "STC"/> <br \>

The heat transfer mechanisms operate simultaneously and interact with each other. Therefore, a useful technique is to derive either an apparent thermal conductivity, <math>K_{eff}</math>, or an effective emittance, <math>\varepsilon^*</math>, through the blanket. We can experimentally derive both the values for steady state heat transfer. <br \>

[[File:PTC Equn.gif|frame|center]]

In satellite applications, the MLI is full of air at launch time. As the rocket ascends through the atmosphere, this air should be able to escape without damaging the blanket. Therefore, holes or perforations are required in the layers, even though this has an associated reduction in effectiveness. <br \>