Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8, 2011. Waseda University, International Conference Center), Tokyo Japan
抄録（英）
Transonic wind tunnel test of a rocket fairing model was conducted to investigate the steady and unsteady phenomena around it and to obtain the experrimental data used for the validation of CFD code. This paper mainly describes the results of the steady and unsteady pressure measurement. The flowfield around the rocket fairing in transonic regime is characterized by shock wave generated downstream the expansion region near the fairing shoulder, separation caused by the shock wave, and suction region behind it. The unsteadiness was observed in the vicinity of the fairing shoulder due to the interaction between the shock wave and the boundary layer. As uniform flow Mach number was increased, the shock wave was moved downstream. In the leewards side with a small angle of attack, the shock wave was moved upstream, the suction region was enlarged, and the stronger unsteadiness was observed. Even the attachment of a tiny shoulder frame to the clean rocket fairing model significantly changed the pressure distribution because the shock wave and the suction region were highly afected. As a result of the frequency analysis, the broadband increase in the power spectrum density of pressure coefficient was observed when the flow passed through the shock wave. No peculiar frequencies relevant to the transonic unsteady phenomena were found.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
ロケットフェアリング模型の遷音速風洞試験
65207033.pdf
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