Engineering calculation of aerodynamic heating for quasi-waverider vehicle

Aiming at the need of integral optimization design of quasi-waverider vehicle (QWV), its aerodynamic heating at boosted and cruise periods was studied based on reference temperature and experience formula. With the aerodynamic heating, thermal radiation and heat conduction of skin, heat flow rate equation was built. By solving this equation, the wall temperature-time relationship of body stagnation and wing leading edge at boosted period, the wall temperature distribution of windward side of body and wing center line at cruise period were obtained. The results show that the temperature of body stagnation region increases rapidly at boosted period, and it will come to balance after entering cruise period. Along body axis direction, boundary layer transition appears, which increases wall temperature. A high Mach number can postpone transition position, and big angle of attack will advance the transition position. This method can be applied to pre-research and multi-objective optimization design of hypersonic QWV.