Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Combined Propulsion Research Group, Kakuda Space Center, Institute of Aerospace Technology
Foundation for Promotion of Japanese Aerospace Technology
The effect of the airframe configuration on the condition of the airflow to an engine was investigated experimentally in a hypersonic flow. Three kinds of forebody models of an aerospace plane were tested in the 1.27-m Mach 9.7 wind tunnel and in the 0.1-m Mach 6.7 pilot-wind tunnel. The leading edge of each model had a different width, that is, a pointed configuration, half of the body width, and the same width as the body. Pitot pressure was measured at the location of the engine entrance. The uniformity of the airflow to an engine was greatest in the model with the longest width at its leading edge. The airflow rate to the engine was large with large width of the leading edge of the airframe. This feature became significant in an engine with large height at the entrance. It was also made clear that the ratio of lift to drag was large in the model with a long leading edge, and that the influence of the shock wave-laminar boundary layer interaction did not spread laterally.
Effect of airframe configuration on condition of airflow to engine in hypersonic flow
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