Numerical and Experimental Study of Hypersonic Shock Interactions in the Launching Phase of Re-usable TSTO Space Transport Vehicle

摘要

Hypersonic aerodynamic heating induced by the complex shock-shock interactions, has been investigated for a next generation TSTO space transport systems. Hypersonic wind tunnel tests have been made by using NAL Mach 10 HWT for the first stage winged vehicle combined with two rocket boosters and heat transfer distributions have been investigated on the booster nose mainly by using JAXA infrared measurement systems. Severe local peak heating is generated on the booster nose by the strong shock wave impingement. In the present Mach 10 conditions, separation shock wave is found on the forward lower fuselage surface generated by the blockage effect of the boosters. This separation shock wave complicates shock interaction flowfields around the booster nose region and oil flow tests are made to clarify these flow structures. Corresponding numerical computations has been made by using overset grid. It is demonstrated that combined study, using both wind tunnel tests and numerical simulations, is essential for the accurate analysis of aerodynamic interactions the ascent phase of next generation space transport systems.