Experimental Study on the Supersonic Flow Around Blunt-Nosed Bodies of Revolution

概要

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The flows around several blunt-nosed bodies of revolution were experimentally investigated over the Mach number range from 3.76 to 4.78 at the intermittent blow-down type supersonic wind tunnel of Aeronautical Research Institute, University of Tokyo. In the present experiment we are concerned with the flow behavior ahead of the bodies so that the interferometric study was primarily made. The main results are summarized as follows : (1) The surface pressure referred to the stagnation pressure, shock-wave pattern, sonicline pattern and flow directions were found to be closely correlated to those found both experimentally and theoretically for the case of the flow with the much higher Mach number than in the present test. (2) The region with the local Mach number lower than 0.5 was confirmed to spread extensively ahead of the nose. (3) The shock-wave detachment distance was found to be nearly independent of the nose shape, when referred to the redius of curvature of the shock wave. (4) For the bodies with the same nose radius, the shock-wave detachment distances were found to be nearly independent of the position of the body shoulders.
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