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为快速高效地计算变前掠翼开裂式方向舵的操纵性能,建立了一种基于面搭接技术的嵌套网格剖分方法,并通过面积加权法建立搭接面两侧的通量守恒关系。然后采用N-S控制方程的有限体积法离散格式,选取SST湍流模型,对襟翼下偏30°的NACA 23012翼型的升阻特性进行数值计算,并与常规分块网格下的数值结果和风洞试验结果作了比较。验证表明:嵌套网格与常规网格的马赫数云图基本一致,襟翼上表面气流分离位置一致,并且均能捕捉到主翼型下端有形成涡的趋势;面搭接及面积加权法能够保证通量守恒传递和计算的精度,该方法简单、便捷,效率较高。最后,采用面搭接技术对变前掠翼开裂式方向舵的升阻特性进行了计算,前掠翼机翼气流流动由翼尖指向翼根,避免翼尖提前失速导致操纵效率急剧下降,面搭接嵌套网格计算方法在变前掠翼性能计算中应用良好。结果表明该方法是操纵面性能计算的一种高效方法。
In order to calculate the maneuverability of the fissile rudder with variable forward swept speed efficiently and effectively, a nested meshing method based on surface overlap technique was established and the conservation of flux on both sides of the lap interface was established by the area weighting method . Then the finite volume method discretization scheme of NS governing equations was used to select the SST turbulence model. The numerical simulation of lift characteristics of NACA 23012 airfoil with 30 ° downward flaps was carried out. Compared with the numerical results of the conventional sub-grid and the wind tunnel test results Made a comparison. The verification shows that the cloud pattern of the nested grids is basically the same as that of the conventional grids, and the airflow separation positions on the upper surface of the flaps are consistent, and the tendency of the vortex forming at the lower end of the main airfoil can be captured. The surface overlap and the area weighting method can ensure Flux conservation and accuracy of the transfer, the method is simple, convenient and efficient. Finally, the lift-drag characteristics of the fissile rudder with anterior swept wing were calculated by face-lap technique. The flow of anterior-swept wing wing was directed from the wing tip to the root of the wing to avoid the premature stall of the wingtip, leading to a drastic drop of maneuvering efficiency. The nested grid calculation method is applied well in the calculation of the forward swept wing performance. The results show that this method is an efficient method for computing the performance of control surfaces.