An investigation of the lift, drag, and pitching moment characteristics of AGARD Calibration Model B has been made in Supersonic Blowdown Wind Tunnel of the National Aerospace Laboraory. The tests covered a Mach number range of 1.5 to 3.0 and a Reynolds number range of 17×16⁶ to 28×10⁶. Comparison with other wind tunnel results shows a good agreement.

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This report is described of the mode of the operation and the characteristics of the hypersonic gun tunnel built at Kyoto University. The theoretical calcutations are presented of the piston motion, vis. the initial motion and the piston deceleration. Experimental results of the stagnation value are compared with the calculational results estimated by the piston motion. The results of measurements of tunnel stagnation and working section conditions are given, and model experiments were performed.

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This paper deals with the technology of shock tunnel used as a hypersonic wind tunnel. The ordinary shock tunnel has a very short running time of about 1 msec., comparing with the other hypersonic facilities. Many methods for increasing the running time are discussed and then the instrumentations for measuring the pressure, force and temperature and so on at the test section are experimentally discussed.

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