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通过耦合求解非定常Euler/Navier-Stokes方程和单自由度滚转运动方程,对带副翼偏转的65°后掠角尖前缘三角翼WI1-SLE自由滚转运动进行了研究,Navier-Stokes方程的求解采用基于Spalart-Allmaras湍流模型的脱体涡模拟(DES)。在多块结构网格上,应用基于弧长的无限插值理论(TFI)生成变形网格,实现副翼偏转,而三角翼的滚转运动则通过网格的整体旋转实现。结果表明:Euler方程和DES方法均准确地模拟出了三角翼在滚转运动过程中存在的3个平衡位置。出现平衡位置的原因分别是:①流动对称性;②机翼左侧发生涡破裂的分离涡与右侧分离涡相互平衡使得滚转力矩为0,并且平衡位置仅与三角翼两侧涡强的差有关;③副翼偏转和左右机翼不对称分离涡涡强差产生的滚转力矩相互平衡。此外,滚转运动对副翼偏角幅值很敏感,幅值的微小改变会影响最终的平衡位置和向平衡位置运动的路径。
The free rolling motion of the WI1-SLE with the tip of the aileron with 65 ° sweep angle was studied by coupling the unsteady Euler / Navier-Stokes equation with the one degree of freedom roll motion equation. The Navier-Stokes The equations were solved using an ex-vivo eddy simulation (DES) based on the Spalart-Allmaras turbulence model. On multi-structured meshes, the deformation mesh is generated by the infinite length interpolation theory (TFI) based on the arc length to realize aileron deflection, while the rolling motion of the delta wing is realized by the overall rotation of the grid. The results show that the Euler equation and the DES method all accurately simulate the existence of three equilibrium positions of the delta wing during roll motion. The reasons for the equilibrium position are: (1) the flow symmetry; (2) the separation vortex with vortex rupture on the left side of the wing and the separation vortex at the right side balance each other so that the rolling moment is 0, and the equilibrium position is only vortex-strong on both sides of the delta wing Poor; ③ ailerons and left and right wing asymmetric separation of the eddy current difference between the rolling torque balance. In addition, roll motion is sensitive to the magnitude of ailerons, and small changes in amplitude affect the final equilibrium position and the path to the equilibrium position.