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
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 flow; Drag and heat reduction; Forward-facing cavity; Counterflowing jet; Maximum thrust nozzle;
机译:超音速流中组合的前向腔和脉冲逆流射流构造引起的阻力和热通量减少机制
机译:由组合前表面腔和超声波流动脉冲和脉冲逆出喷射配置引起的拖曳和热通量降低机构
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:稀土流量逆流射流热通量降低机理的数值研究
机译:对钝基体上船尾基腔减阻机理的研究。
机译:浅腔中的层流壁射流和传热
机译:逆流射流及其组合对超音速流量的阻力和热减少调查
机译:用逆流喷射预测超音速和高超声速流动中的减阻