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利用CFD软件FLUENT,对亚声速条件下一种可变弯度的变形翼进行了数值仿真,捕捉到了翼型表面局部激波现象,给出了翼型气动参数与翼面激波位置随弯度变化的曲线图,并分析了弯度变化对其的影响。结果表明,翼型弯度发生变化时,激波在翼面的位置会发生改变,并对翼型气动参数产生较大影响;适度减小翼型的弯度,对激波影响有一定的改善作用。分析结果为变形翼的优化设计和变形飞行控制提供了理论与数据支持。
A CFD software FLUENT was used to simulate a variable camber deformation wing under subsonic velocities to capture the localized shocks on the airfoil surface. The aerodynamic parameters of airfoils and the variation of shock wave position with airfoil were given Curve, and analyzed the impact of changes in camber. The results show that when the airfoil curvature changes, the position of the shock wave on the airfoil will change, and the aerodynamic parameters of the airfoil will be greatly influenced. The airfoil curvature will be moderately reduced, which will improve the impact of the shock wave. The analysis results provide theoretical and data support for the optimal design of the deformation wing and the deformation flight control.