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针对一种简化的飞机模型,数值模拟了推力矢量尾喷流与高速主流的干扰效应,系统总结了来流马赫数、攻角、喷管偏转角、喷流马赫数、喷流总压、喷流总温等参数对飞机气动特性的影响规律,分析了流动机理,结果表明:对于该简化战斗机模型,推力矢量尾喷流对高速主流的干扰局限于尾部局部区域,对全机气动特性的影响较小,仅在较大攻角下才有一定体现;但高速主流对尾喷流的干扰显著,推力矢量角损失随来流马赫数和攻角的增大而增大。
Aiming at a simplified aircraft model, the thrust vectorial jet and the high-speed mainstream are numerically simulated. The Mach number, angle of attack, nozzle deflection angle, Mach number, jet pressure and jet pressure Flow total temperature and other parameters of the aircraft aerodynamic characteristics of the flow mechanism, the analysis of the flow mechanism, the results show that: for the simplified fighter model, thrust vectorial jet flow on the mainstream of high-speed interference is limited to the tail of the local area, the whole aerodynamic characteristics But only at larger angles of attack. However, the interference of the high-speed main stream to the tail jet is significant, and the thrust vector angle loss increases with the increase of the Mach number and the angle of attack.