SIMULATION OF SHOCK-INDUCED COMBUSTION PAST BLUNT PROJECTILES USING SHOCK-FITTING TECHNIQUE

Two-dimensional axisymmetric, reacting viscous how over blunt projecti les is computed to study shock-induced combustion at Mach 5.11 and 6.4 6 in hydrogen-air mixture. A finite difference, shock-fitting method i s used to solve the complete set of Navier-Stokes and species conserva tion equations. In this approach, the bow shock represents a boundary of the computational domain and is treated as a discontinuity across w hich Rankine-Hugoniot conditions are applied. All interior details of the flow such as compression waves, reaction front, and the wall bound ary layer are captured automatically in the solution. Since the shock- fitting approach reduces the amount of artificial dissipation, all int ricate details of the flow are captured much more clearly than has bee n possible with the shock-capturing approach. This has allowed an impr oved understanding of the physics of shock-induced combustion over blu nt projectiles and the numerical results can now be explained more rea dily with a one dimensional wave-interaction model.