论文部分内容阅读
对装有“前端襟翼”和“前缘襟翼”的７４°后掠三角翼的不可压缩流场作了数值模拟，以研究襟翼的旋涡控制作用．数值模拟是用拟压缩性方法求解一般曲线坐标系下的三维不可压缩Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，时间离散用向后Ｅｕｌｅｒ差分，空间无粘项的离散用二阶迎风ＴＶＤ格式，所得的离散方程用对角化形式的近似隐式因子分解格式求解．湍流模型用Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数模式．计算了三种平面形状的机翼在迎角范围为１０°～５０°的绕流和气动特性．计算和实验的比较表明，襟翼向下偏转可以推迟旋涡破裂，且对提高机翼的减阻能力、升阻比和改善失速前后的气动特性有明显效果，双襟翼具有更佳的控涡效果．
The incompressible flow field of 74 ° sweep wing with “front flaps” and “leading flaps” was numerically simulated to study the vortex control action of flaps. The numerical simulation is to solve the three-dimensional incompressible Navier-Stokes equations in the general curvilinear coordinate system by the method of quasi-compressibility, the backward second-order upwind TVD scheme with the backward Euler difference and the non-sticky item in time dispersion, and the resulting discrete equation Approximate Hidden Factorization Format Solution of Kinked Forms. Baldwin-Lomax algebraic model for turbulence models. The flow and aerodynamic characteristics of the three kinds of plane wings at 10 ° ~ 50 ° angle of attack were calculated. The comparison of calculation and experiment shows that downward deflection of flaps can delay the vortex rupture and has obvious effect on improving drag reduction, lift-drag ratio and aerodynamic characteristics before and after stalling, and double-flap has better control vortex effect.