鸭翼展向吹气涡控技术增升特性研究

A study on lift-enhancement with vortex control technique of canard-spanwise blowing

利用低速风洞测力实验，对一个机翼前缘后掠角为40°的近距耦合鸭式布局简化模型，系统研究了不同鸭翼前缘后掠角和鸭翼展向吹气量对该布局增升量值的影响，给出了不同迎角下升力系数和增升量值随鸭翼前缘后掠角和鸭翼展向吹气动量系数的变化曲线。结果表明：在一定迎角范围内（16°-50°），对于不吹气情况，鸭翼前缘后掠角越大，布局的增升量越大，说明鸭翼作为涡控制部件是合适的；当对鸭翼进行展向吹气时，吹气动量系数越大，布局的增升量也越大，说明利用鸭翼展向吹气技术达到间接控制机翼涡，延迟机翼涡的破裂，增加机翼的升力是完全可行的。

A wind-tunnel force measurement experiment was undertaken to investigate the effect of canard sweeps and momentum coefficients of canard-spanwise blowing on lift-enhancement over simple close-couple canard-configurations with 40° swept delta-wing. The curves of lift coefficient and lift coefficient increment are presented at different attack angles. It can be found that： at certain range of attack angles （16°- 50°）, the magnitudes of lift-enhancement increase with canard sweeps when no blowing, which shows that the canard can be used as a element for controlling the vortex ; the magnitudes of lift-enhancement increase with blowing momentum coefficients when blowing, which suggests that the indirectly controlling the wing vortex, delaying its breakdown and increasing the lift with the technique of canard-spanwise blowing for close-couple canard-configurations are possible.