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为预估任意栅翼结构的气动系数,推导并使用了可压缩涡系表达式。为了验证这种理论,在低速风洞中对某些有代表性的栅翼设计方案作了实验。实验结果表明,对多数栅翼设计方案来说,法向力和翼根弦的弯矩都是非线性的,以致看起来当攻角不同时,翼面的上下表面趋于失速状态。在整个攻角范围内,铰链力矩都较小,阻力系数不一定是抛物线性的。对多数结构来说,实验数据与理论数据非常一致。
To estimate the aerodynamic coefficient of any gimbal structure, a compressible vortex system expression is derived and used. In order to validate this theory, some representative gimbal designs have been tested in low speed wind tunnels. The experimental results show that for most of the design of the gimbal, the moment of normal force and wing root chord are nonlinear, so that it appears that when the angle of attack is different, the upper and lower surfaces of the airfoil tend to stall. The hinge moment is small throughout the angle of attack, and the drag coefficient is not necessarily parabolic. For most structures, the experimental data are in good agreement with the theoretical data.