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对细长锥体分离涡稳定性判据进行了介绍,并应用该判据对细长体平板三角翼和加上两个不同高度背鳍组合体分离涡流场的稳定性进行了分析。为了验证理论分析的有效性,并观察气动力随迎角的变化,根据理论分析模型设计了实验模型,并在低速风洞进行了六分量天平测力实验,三角翼后掠角为82.5°,实验迎角范围12°～32°,侧滑角范围-10°～+10°,实验雷诺数1.66×106。实验结果表明:在翼面上发生旋涡破裂前,单独细长平板三角翼的横向力/力矩在实验迎角范围内始终为零;加了两个不同高度的背鳍后,在一定迎角下,三角翼的横向力/力矩变得不为零。理论分析结果和实验结果在定性上吻合得很好,初步验证了有关文献关于细长锥体分离涡的稳定性理论。
The stability criteria for the separation of eddies of slender pyramids are introduced and the stability of the separation eddies field of the slender delta wings combined with the two different heights of the dorsal fin combined with the criterion is analyzed. In order to verify the validity of the theoretical analysis and observe the variation of the aerodynamic force with the angle of attack, the experimental model was designed according to the theoretical analysis model and the six-component force measurement experiment was carried out in the low-speed wind tunnel. The delta wing sweep angle was 82.5 °, The experimental range of attack angle is 12 ° ~ 32 °, the range of side slip angle is -10 ° ~ + 10 °, and the experimental Reynolds number is 1.66 × 106. The experimental results show that the transverse force / moment of single slender flat delta wing is always zero within the experimental angle of attack before the vortex rupture occurs on the airfoil. After adding two dorsal fins of different heights, Delta wing lateral force / moment becomes non-zero. The theoretical analysis and experimental results are in good agreement with each other qualitatively, which proves the stability of the literature about the separation vortex of slender pyramids.