非均匀来流下飞翼布局气动特性模拟方法研究

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。

Research on Flying Wing Aerodynamic CharacteristicsUnder Non-uniform Coming Flow

Based on unsteady Navier-Stokes equations, the aerodynamic response of aircraft in non-uniform flow is investigated through introduction of the grid velocity. First, the aerodynamic characteristics of typical NACA0006 airfoil was simulated in non-uniform flow applying this developed method. It is shown that the calculated lift responses of the airfoil agree well with calculated value in reference. This example verified the accuracy of the development simulation method of aircraft aerodynamic characteristics in non-uniform flow. Furthermore, the aerodynamic response process of flying wing in non-uniform flow was simulated by this method. The distribution curve of aircraft lift coefficient with the phase angle is calculated and analyzed in different velocity perturbation ratio. The results show the aerodynamic characteristics of aircraft in non-uniform flow are become obvious when the velocity perturbation ratio is larger.