Hypersonic CFD Solutions for Boundary-Layer Transition Sled Test Track Experiment

In this study, we have performed simulations on blunt ogive geometries at various hypersonic speeds. The primary objective of conducting these simulations is to obtain the shapes of shock waves and pressure distributions, which are intended for use with the Harris Boundary-Layer Code developed by NASA. By leveraging the synergy between the Computational Fluid Dynamics (CFD) simulations, the Harris Code, and a 1D Heat Conduction Code, we aim to predict the surface roughness that leads to Boundary-Layer Transition. Specifically, we have evaluated the blunt ogive geometries at Mach 6 and 8 speeds. The details of this process, from geometry generation to post-processing of the results, will be explained in depth, utilizing the ANSYS Fluent Software as our primary tool.