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乘波体构型是高超声速飞行器的重要气动布局之一。对某多目标优化设计的乘波体构型飞行器进行了高超声速测压实验,对其气动性能进行风洞实验验证。实验马赫数M=6和M=7,迎角α=-4°-、2°、0°、2°、4°、6°、8°。结果表明:该乘波体构型各部件气动性能良好。进气道唇口准确捕捉到压缩激波,激波位置与设计吻合。乘波体上表面流向压力变化不大,有利于减小乘波体飞行阻力。下表面经过进气口内压段时压力有明显的增大,后体膨胀效果显著。在设计状态下,该乘波体飞行器整体气动性能良好。
Waveform configuration is one of the most important aerodynamic layouts for hypersonic vehicles. A hypersonic pressure measurement experiment was conducted on a multi-target optimized design of multiply-wave structure aircraft, and its aerodynamic performance was verified by a wind tunnel experiment. Experimental Mach number M = 6 and M = 7, angle of attack α = -4 ° -, 2 °, 0 °, 2 °, 4 °, 6 °, 8 °. The results show that the aerodynamic performance of each component of the multiplicative wave structure is good. Inlet lip accurately capture the compression shock wave, shock wave position and design coincide. By the wave body on the surface flow pressure is not changed, help to reduce the wave body flying resistance. Under the surface after the pressure within the inlet section pressure significantly increased, significant effect of body expansion. Under the designed state, the overall aerodynamic performance of the multiply-multiply aircraft is good.