Institute of Space and Aeronautical Science,University of Tokyo
雑誌名
ISAS report/Institute of Space and Aeronautical Science,University of Tokyo
巻
30
号
3
ページ
83 - 100
発行年
1965-01
抄録（英）
First the flow survey is made for the low-density hypersonic flow, which is achieved by a low-density operation of the gun tunnel (or free piston compression). In particular the measurements of flow velocity and, hence, of stagnation temperature are worked out by means of an explosion-wire technique and the flow survey done by traversing a free molecule calorimeter in the test flow region. With these diagnostics the characteristic feature of the test flow is investigated. It is found that, by a low-density operation of the present gun tunnel, the test flow of Mach number 10 and Reynolds number 650 (per cm) is achieved, which is applicable to experimental studies on low-density hypersonic flow problems. Secondly an experimental study is made concerning the shock-layer structure ahead of a sphere in a low-density hypersonic flow, achieved by the present gun tunnel. The scanning-electron-beam densitometer is developed to obtain a density distribution along a scanning path of the beam during one shot of the gun tunnel. By means of this device the density distribution across the shock layer is measured for a sphere of 12.4mm in radius, in which case the Reynolds Re_∞ is about 800. The present data exhibit a qualitative agreement with Lcvinsky-Yoshihara profile which was computed for argon flow of Mach number M=10 and Re_∞=10^3 and 10^2.
Experimental Studies in a Low Density Gun Tunnel Stream
SA2400496.pdf
(1.16MB)
