作为平均迎角趋于零的特殊情况，本文的数值结果与超声速线化的位流理论是一致的，在高超声速情况与活塞理论一致。
Numerical solutions agree with supersonic linearized potential flow theory as a special case when the mean angle of attack tends to zero and with piston theory in hypersonic case.
亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
通过理论分析、实验测量和数值模拟，研究高超声速粘性相互作用对实验段自由流静压测量的影响。
Hypersonic viscous interaction effects on measurement of free stream pressure in test section are studied through theoretical analysis, experiment measurement and numerical simulation.
应用推荐