机译:高扫掠微斜坡控制高超声速进气口的冲击/边界层相互作用
Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;
Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;
Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;
Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;
机译:高超音速进气口中严重冲击波/边界层相互作用的控制
机译:凹凸不平控制高超声速进气道的风罩冲击/边界层相互作用
机译:正常冲击/边界层相互作用的微匝流控制
机译:超音速入口压缩坡道冲击波/边界层相互作用的大涡模拟
机译:高超声速扫掠边界层相互作用的实验研究。
机译:高超声速低密度流中冲击相互作用的DSMC模拟和实验验证
机译:马赫数对扫描冲击波/边界层相互作用的锥形表面特征的影响
机译:一些控制体积技术在超音速入口冲击 - 边界层相互作用分析中的应用