油流技术在常规风洞中的应用已很广泛,但是,在诸如激波风洞等脉冲型设备中却几乎见不到它。流动分离足空气动力学中最重要的研究课题之一。本文介绍了高超声速激波风洞中油流技术和圆柱前紊流边界层分离的初步研究结果。试验是在0.6米激波风洞中进行的。喷管出口的自由流条件是:M=7.94,Re/L=2.79×10~7(1/米)。风洞试验时间约7毫秒。对试验结果作了讨论,并与国外结果作了比较。 Oil flow technology has been used extensively in conventional wind tunnels, but barely visible in impulsive devices such as shock wind tunnels. Flow separation One of the most important research topics in foot aerodynamics. This paper presents the preliminary results of the oil flow technique in hypersonic shock wind tunnel and the separation of the boundary layer of the cylinder before turbulence. The test was conducted in a 0.6 meter shock wave wind tunnel. The free flow conditions at the nozzle exit were: M = 7.94, Re / L = 2.79 × 10 -7 (1 / m). Wind tunnel test time is about 7 milliseconds. The test results were discussed and compared with foreign results.