24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-3.3.3

BOUNDARY-LAYER TRANSITION MEASUREMENTS ON AN AXISYMMETRIC BODY AT INCIDENCE AT SUPERSONIC SPEED

H. Sugiura
Japan Aerospace Exploration Agency, Japan

Keywords: transition, axisymmetric body, infrared camera, pressure transducer

Transition measurements on an axisymmetric nose model at small incidence were conducted at Mach 1.2. Transition charcteristics were obtained using an infrared camera and an unsteady pressure transducer. The results show that both stationary and traveling crossflow waves were observed at 1-deg incidence on the side.

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