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在中航气动院FL-9低速风洞中,进行了飞艇尾翼脉动压力特性实验研究。测量了尾翼的脉动压力,着重分析了各测量点的脉动压力系数、频谱和相关性系数等特性。结果表明:脉动压力系数由尾翼前缘向后缘逐渐增大。尾翼的中部和前缘脉动压力系数随迎角无明显变化,在迎角超过8°以后,尾翼后缘的脉动压力系数随迎角增大而急剧增加。连续变迎角测量结果与固定迎角测量结果相比,脉动压力系数产生了明显的迟滞特性。尾翼上表面脉动压力的自相关系数和互相关系数从前缘到后缘逐渐降低,且前缘表现出显著自相关性,下翼面脉动压力基本互不相关。
In the FL-9 low-speed wind tunnel of Pneumatic Court of China Aviation Aeronautical Institute, experimental research on the pulsating pressure characteristics of the airship tail was carried out. The pulsating pressure of the tail was measured. The characteristics of pulsating pressure coefficient, frequency spectrum and correlation coefficient of each measuring point were analyzed emphatically. The results show that the pulsating pressure coefficient gradually increases from the leading edge of tail to the trailing edge. The pulsating pressure coefficient at the middle and leading edge of the tail wing did not change significantly with the angle of attack. After the angle of attack exceeded 8 °, the fluctuating pressure coefficient at the trailing edge of the tail increased sharply with the angle of attack. Continuous variable angle of attack measurements Compared with the results of fixed angle of attack measurements, pulsatile pressure coefficient has a significant hysteresis characteristics. The autocorrelation coefficient and cross-correlation coefficient of the pulsating pressure on the upper surface of the tail gradually decreased from the leading edge to the trailing edge, and the leading edge showed significant autocorrelation. The fluctuating pressure of the lower wing surface was basically irrelevant.