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飞翼布局的非均匀来流会使得飞翼的流场不均匀,从而影响其气动性能。通过引入“网格速度”来计入非均匀来流的影响,求解非定常Navier-Stokes方程,实现了非均匀来流下飞翼布局气动特性的数值模拟。首先采用该方法对NACA0006翼型非均匀来流下的气动力响应进行了计算,计算结果与文献计算结果吻合良好。进一步对某飞翼布局飞机在非均匀来流下的气动力响应过程进行了数值模拟,得到了不同振荡速度比率下飞翼布局气动力系数随相位角变化曲线,结果表明,振荡速度比率越大,升力响应的幅值越大,非均匀来流对飞行器气动特性影响越明显。
The non-uniform flow of the flying wing layout will make the flow field of the flying wing inhomogeneous and thus affect its aerodynamic performance. By introducing “grid velocity ” to account for the influence of non-uniform flow, the unsteady Navier-Stokes equations are solved and the numerical simulation of the aerodynamic characteristics of the non-uniform flow field is realized. Firstly, the aerodynamic response of NACA0006 airfoil with non-uniform airfoil flow is calculated by this method. The calculated results are in good agreement with the literature. The aerodynamic response of a flying wing aircraft in non-uniform flow is numerically simulated. The aerodynamic coefficients with different oscillation speed ratios are obtained. The results show that the larger the oscillation speed ratio, The greater the magnitude of the lift response, the more significant the effect of non-uniform flow on aerodynamic characteristics of the aircraft.