Effects of Crack on Heat Flux in Hypersonic Shock/Boundary-Layer Interaction

摘要: A small crack on body surface led to a tragic accident in 2003, which is the Columbia accident. During shuttle's re-entry, high temperature gas penetrated leading-edge of left wing and melted aluminum structure, finally blew up. Since early times, there are many fundamental studies about simple cavity-flow formed hypersonic speeds. However, an investigation Shock/Boundary-Layer Interaction (SBLI) has not been researched. For multistage space transportation vehicle such as TSTO, SBLI inevitable problem, then becomes critical issue for TSTO development. In this study, effects crack, where occurs, were investigated speed (M∞ = 8.1). square locates at point booster. Results show that its depth strongly effect peak heat flux aerodynamic interaction flow-field. cases shallow (d/C ≤ 0.10), exist two regions floor, flow reattachment region back end wall crack. case, 2 times large stagnation flux, value larger compared with case No-Crack TSTO. While deep 0.20), overall floor decreases below flux. These results provide useful data development thermal protection system (TPS) tile.