LXVIII. Experiments on separation of boundary layers on probes in front of blunt-nosed bodies in a supersonic air stream
LXVIII. Experiments on separation of boundary layers on probes in front of blunt-nosed bodies in a supersonic air stream
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DOI：
10.1080/14786440708520987
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发表时间：
1952-07
期刊：
影响因子：
--
通讯作者：
W. A. Mair
中科院分区：
文献类型：
--
作者：
W. A. Mair
摘要如果钝头旋转体在头部安装细长的探头，并置于超音速气流中，则在机身前方的激波和探头上的边界层之间存在相互作用。这类流动的纹影照片是在马赫数为1.96的半球形扁平机头和不同长度的探头的旋转体上拍摄的。在半球形鼻体上进行了一段探头的压力分布测量。当探头长度大于1 1/2体径时，边界层在探头头部附近分离，形成近圆锥形的死气区。在这种情况下，两种形状的物体都会出现这种流动，阻力比没有探头时要小得多。对于较大的探头长度，边界层在探头后分离，而死气区的形状和激波模式取决于分离点的边界层是层流还是湍流。
Summary If a blunt-nosed body of revolution is fitted with a slender probe at the nose and placed in a supersonic air stream, there is an interaction between the shock wave in front of the body and the boundary layer on the probe. Schlieren photographs of this type of flow were taken for bodies of revolution with hemispherical and flat noses and various lengths of probe, at a, Mach number of 1 ·96. Measurements of pressure distribution were also made on the hemispherical-nosed body for one length of probe. With a probe length of abotut 1 1/2 body diameters, the boundary layer separates near the nose of the probe and a nearly conical dead-air region is formed. With this type of flow, which occurs with both shapes of body, the drag is considerably less than it is without a probe. For greater probe lengths the boundary layer separates behind the nose of the probe, and the shape of the dead-air region and shock-wave pattern depend on whether the boundary layer is laminar or turbulent at the point of separatio...