机译:超声速流中入射激波与横向缝隙注入相互作用的数值预测
Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha,Hunan 410073, People's Republic of China;
Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha,Hunan 410073, People's Republic of China;
Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha,Hunan 410073, People's Republic of China;
Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha,Hunan 410073, People's Republic of China;
Aerospace propulsion system; Transverse slot injection; Incident shock wave; Ramp; Supersonic flow;
机译:平面超音速射流中边界层冲击波相互作用的数值模拟
机译:超声速横流中多喷嘴喷射器阵列对横向射流冲击波相互作用的数值研究
机译:湍流模型和缝隙宽度对超声速流动中横向缝隙注入流场的影响
机译:横向声速射流与超音速湍流冲击波的相互作用及感应
机译:通过环形管道(SCRAMJET)进行超音速流场中冲击波和湍流边界层相互作用的实验研究。
机译:超音速腔流动的数值激光能量沉积和控制流动的传感器放置策略
机译:具有冲击波的超声内部流动研究 - 二维通道中mach 2伪激波的内部结构数值分析研究
机译:超声速流中横向注入的相互作用冲击形状