Turbulence measurements in a three-dimensional boundary layer in supersonic flow

摘要: Turbulence measurements were obtained in a three-dimensional supersonic turbulent boundary layer. A 20° curved fin was used to generate compression of layer at Mach 3 the absence shock waves. Data include hot-wire five components Reynolds stress tensor. The results are interpreted terms mean flow field history turbulence. It is demonstrated that in-plane curvature can have strong stabilizing effect on