机译:高超音速飞行器组合式对置射流和声腔概念的减阻和降温机制
Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
Hypersonic vehicle; Drag reduction; Heat release reduction; Opposing jet; Acoustic cavity; Supersonic flow;
机译:超音速流中新型腔与反射流组合的阻力和热通量降低效率性能参数研究
机译:高超声速流中新型腔体与逆流射流概念相结合引起的减阻减热机理
机译:高超音速流动中新型尖刺钝体和后部对置射流概念的减阻降热参数研究
机译:可变钝性超音速车辆的多孔对置射流的减阻机理
机译:对钝基体上船尾基腔减阻机理的研究。
机译:非常规设计的跟踪环适用于超音速车辆的等离子护套通道
机译:用上游能量沉积和超音速流动的组合减少的参数研究
机译:检验海洋动物减阻机制,潜在应用于无人驾驶飞行器