Modeling the Effects of Geometric Asymmetry on Aero-heating of the Ablative Noses

The purpose of the proposed research methodology is to improve the temperature contour calculations of aeroheating code (CTCA) for the Asymmetrical and noncircular ablative noses by using the equivalent axisymmetric body (EAB) theory. This Code has been developed by researchers and the results of it have been validated by the various flight tests results. In the case of non-zero angle of attack or asymmetric surface ablation for each meriodinal plane, the equivalent meriodinal plane (EMP) is created for any meriodinal plane. The combinations of these planes constitute the EAB. The governing equations are solved for this body by using the non-equilibrium chemical reactions and the results of it are mapped to the main body. The solving of a typical nose during flight trajectory show that the convergence of this technique is very fast as compare to the user defined function (UDF) based on the fluent solvers. The results of this research are validated by the UDF and the relative error of it is less than 10 percent.