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通过风洞测力实验研究了平面形状(后掠角)对展长/根弦长之比为1.0的机翼的气动特性的影响,实验结果表明,模型后掠角在很大程度上影响小展弦比机翼的气动特性,当模型后掠角Λ≤35°时,能增大模型的最大升力系数和失速迎角,推迟失速;当模型后掠角Λ=56°~64°时,能得到较好的升力曲线,改善机翼的失速特性。此外,实验结果表明模型前缘背风面倒角与迎风面倒角相比,有效地提高了模型的最大升阻比和失速后的升力系数。
The influence of the plane shape (sweep angle) on the aerodynamic characteristics of the wing with the ratio of the length of the root to the length of the chord of 1.0 was studied by wind tunnel force test. The experimental results show that the model sweep has a great influence on the aerodynamic performance Aspect ratio wing aerodynamic characteristics, when the model sweep angle Λ ≤ 35 °, can increase the maximum lift coefficient of the model and stalling angle of attack, postponed stalling; when the model sweep Λ = 56 ° ~ 64 °, Get a better lift curve to improve the stall characteristics of the wing. In addition, the experimental results show that compared with the windward chamfer, the leeward of the leeward front of the model effectively increases the maximum lift-drag ratio and the lift coefficient after stalling.