机译:诱导边界层过渡研究的超音速风洞设计与鉴定
Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Chaussee de Waterloo 72, Rhode-Saint-Genese 1640, Belgium;
Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Rhode-Saint-Genese, Belgium;
Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Rhode-Saint-Genese, Belgium;
Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Rhode-Saint-Genese, Belgium;
Department of Fluid Mechanics, Polytechnic University of Catalonia, Terrassa, Spain;
Supersonic flow; wind tunnel qualification; freestream fluctuations; boundary layer transition; measurement techniques;
机译:存在传热和空气吸入的轴对称航空物理飞行复合体和风洞模型中超音速边界层的层流湍流过渡研究
机译:超声速静音风洞边界层吸力装置的数值模拟设计
机译:喷嘴几何形状对超音速风洞角边界层的影响
机译:过渡实验超音速风洞的设计与鉴定
机译:人工感应湍流对边界层过渡在超声速流动中的影响。
机译:具有两个网状电极的等离子体致动器的风洞测试在大角度下边界层控制
机译:超声速风洞诱导边界层过渡研究的设计与鉴定
机译:LUT火炮隧道中的平板边界层过渡;超音速和高超音速马赫数下火炮隧道与常规风洞数据的过渡辐射气动噪声相关性