Abstract: To understand the mechanism of oscillatory flow of the airbreathing hypersonic propulsion in booster stage, unsteady numerical simulations of the axisymmetric airbreathing hypersonic propulsion under blind cavity condition were conducted with the “dual-time-step” scheme. The obtained result demonstrates that shock wave oscillations reliably appear in inner flowpath of the vehicle and pressure on the wall of the inner flow path varies periodically with low frequency and high amplitude. Then, the flow-through scheme of the interstage was designed. Steady and unsteady numerical simulations were conducted to the integrated flow of the vehicle, and the obtained result shows that shock wave oscillation disappears.

Key words: Airbreatming hypersonic propulsion; Integration of inner and outer flow; Shock wave oscillation; Numerical simulation

摘要： 为了掌握高超声速飞行器盲腔流场的激波振荡机理,采用“双时间步”方法对轴对称吸气式高超声速飞行器内流道盲腔流场进行了非定常数值模拟。结果表明,飞行器内流道出现了非定常激波振荡现象,内流道壁面压力出现了低频高幅的周期性变化。为了消除高超声速飞行器内流道的激波振荡现象,设计了级间段泄流方案,对飞行器进行了内外流一体化定常和非定常的数值模拟。结果表明,级间段泄流方案可以有效地消除内流道的激波振荡现象。

关键词: 高超声速飞行器;内外流一体化;激波振荡;数值模拟