High-Order Shock-Fitting Method for Hypersonic Flow with Graphite Ablation and Boundary Layer Stability

A high-order shock-fitting method with thermochemcial nonequilibrium and finite rate boundary conditions for graphite ablation is presented. The method is suitable for direct numerical simulation of boundary layer stability with graphite ablation. Validation with three computational data sets and one set of experimental data is shown. Stability results of the method for a 7 half angle blunt cone at Mach 15.99 are compared with ideal gas computations that set their wall temperature and wall blowing from the real gas simulation. Weak planar fast acoustic waves are used to perturb the steady base flow. In the nose region wall normal velocity fluctuations increase three orders of magnitude and then decrease rapidly as the wall mass flux decreases on the cone surface. In the nose region perturbation amplitudes of vibration temperature are two orders of magnitude larger than perturbation ampitudes of translation-rotation temperature.