| 沈彦杰*,卜忱,杜希奇,贲宝佳.飞艇尾翼脉动压力特性实验研究[J].实验力学,2015,30(1):82~86 |
| 飞艇尾翼脉动压力特性实验研究 |
| Experimental Study of Fluctuating Pressure Characteristics on Airship Empennage |
| 投稿时间：2014-03-02 修订日期：2014-06-26 |
| DOI：10.7520/1001-4888-14-036 |
| 中文关键词: 脉动压力 频谱 相关性系数 |
| 英文关键词:fluctuating pressure frequency spectrum correlation coefficient |
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| 中文摘要: |
| 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。 |
| 英文摘要: |
| Experimental study of fluctuating pressure characteristics on airship empennage was conducted by using FL-9 low-speed wind tunnel in China Aerodynamics Research Institute of Aeronautics. Fluctuating pressures on empennage were measured; the pressure coefficients were obtained from different measurement points; the frequency spectrum and correlation coefficient of fluctuating pressure were analyzed. Results show that the fluctuating pressure coefficients gradually increase from the front edge to the trailing edge of empennage. The fluctuating pressure coefficients in the middle and front regions of empennage have no obvious change along with the increase of angle of attack. When attack angle is larger than 8 °, the fluctuating pressure coefficients at trailing edge of empennage increase rapidly with the increase of attack angle. The comparison between measurement results obtained under both conditions of attack angle continuous variation and at a fixed attack angle respectively shows that fluctuating pressure coefficient presents obvious hysteresis characteristics. From the front edge to trailing edge on the upper surface of empennage, the autocorrelation coefficient and cross-correlation coefficient decrease gradually. The front edge presents significant autocorrelation, the fluctuating pressures on the lower surface of empennage are basically irrelevant. |
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