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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1993, Vol. 14 ›› Issue (8): 394-397.
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Xu Ke-fa, He Long-de, Li Ming-juan, Cheng Shu-hua
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Abstract: This paper describes a wind tunnel free-flight technique for measuring pitch-damping derivatives of a missile model at high angles of attack. The tests were performed in a 20cm by 20cm supersonic wind tunnel with free-stream Mach number of 2.0. Test model is a basic finned configuration. The model was released by a pneumatic launcher. The maximum angle of attack of 100 degrees can be achieved in free-flight testing. Model trajectories were recorded by a high-speed drum camera. Pitch-damping moment derivatives versus angles of attack were obtained by numerical integral method.
Key words: wind tunnel free-flight, high angles of attack, stability derivatives, data processmg
Xu Ke-fa;He Long-de;Li Ming-juan;Cheng Shu-hua. EXPERIMENTAL INVESTIGATION OF DYNAMIC STABILITY DERIVATIVES AT HIGH ANGLES OF ATTACK IN WIND TUNNEL FREE-FLIGHT[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1993, 14(8): 394-397.
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https://hkxb.buaa.edu.cn/EN/Y1993/V14/I8/394