Wind tunnel test investigation on buffeting characteristics of horizontal tail of commercial aircraft in low-speed cruise configuration
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摘要: 提出一种分析平尾抖振的风洞试验方法，通过在某型常规布局民用客机刚性全模的主翼和平尾表面安装超小型脉动压力传感器，测量并分析了主翼及平尾表面脉动压力的时域与频域数据，得到了在主翼尾流及自身流动特性影响下平尾不同截面的脉动压力特性和表面压力分布特性。结果表明：在中小迎角下，主翼出现强分离流动时产生的随机脉动压力激励会引起平尾结构强迫振动，且平尾表面的脉动压力主频与主翼尾流的脉动压力主频相近。在大迎角下，平尾不再受主翼尾流的干扰，其脉动压力特性与自身的分离特性相关，且沿平尾展向向外脉动压力功率谱密度值逐渐降低。Abstract: In this paper, a wind tunnel test method is proposed to analyze the buffeting of the horizontal tail. By installing subminiature pulsating pressure sensors on the wing and horizontal tail surface of a commercial aircraft with conventional layout, the time domain and frequency domain data of the pulsating pressure on the wing and horizontal tail surface are measured and analyzed. The test results show the characteristics of fluctuating pressure and surface pressure distribution under the influence of the wing wake and its own flow characteristics on different sections of the horizontal tail. The results show that the structural forced vibration of the horizontal tail is induced by the random fluctuating pressure excitation generated by the strong separated flow of the wing at medium and small angles of attack, and the dominant frequency of the fluctuating pressure on the horizontal tail surface is close to that of the vortex on the main wing. At large angles of attack, the horizontal tail is no longer disturbed by the wake of the main wing, its fluctuating pressure characteristics are related to its own separation characteristics, and the power spectral density of the fluctuating pressure decreases gradually along the spanwise direction of the horizontal tail.
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Key words:
- commercial aircraft /
- horizontal tail /
- wind tunnel test /
- fluctuating pressure
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图 3 主翼尾缘脉动压力随迎角的变化
Figure 3. Variation of fluctuation pressure at trailing edge of main wing with angle of attack
图 4 平尾30%展向截面近前缘处脉动压力及上表面压力分布随迎角的变化
Figure 4. Variation of pressure distribution on horizontal tail surface and fluctuation pressure at leading edge of 30% span-wise section with angle of attack
图 5 平尾51%展向截面近前缘处脉动压力随迎角的变化
Figure 5. Variation of pressure distribution on horizontal tail surface and fluctuation pressure at leading edge of 51% span-wise section with angle of attack
图 6 平尾92%展向截面近前缘处脉动压力随迎角的变化
Figure 6. Variation of pressure distribution on horizontal tail surface and fluctuation pressure at leading edge of 92% span-wise section with angle of attack
表 1 右平尾上表面13个传感器的位置
Table 1. Position of 13 sensors on the upper surface of the right horizon- tal tail
y/b 0.92 0.51 0.30 x/c 0.10 0.10 0.10 0.20 0.20 0.20 0.35 0.54 0.54 0.54 0.75 0.75 0.75 
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表 2 右主翼上表面1个传感器的位置
Table 2. Position of 1 sensor on the upper surface of right main wings
y/b 对应平尾92%截面位置 x/c 接近主翼面后缘
下载: 导出CSV
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