Conjugate Heat Transfer Analysis in a Hypersonic Flow

Abstract

Transient heat transfer analysis is very significant and has scientific relevance to understand the flow in hypersonic applications. The present studies mainly focus on the effects of experimental time scale and substrate properties on the thermal penetration of the heat into the aerodynamic surfaces. The problem is addressed though conjugate heat transfer (CHT) analysis. The main observation of present analysis is that near the sensor region (stagnation point), heat penetration is less as compared to SiC and carbon-carbon region. Temperature rise is more significant in the sensor region. Stagnation-point heat flux is seen to be largely decreased due to maximum rise in the wall temperature in that region. The CHT analysis has the capability of predicting heating rates at any locations on the aerodynamic surfaces with multiple wall materials and can be used as tool for selection material and design of hypersonic configurations.