大展弦比飞机翼身Euler绕流计算

Calculation for Large Aspect Ratio Wing-Body Flow Using Euler Code

给出了用Euler方程对大展弦比翼身组合体绕流的数值模拟，将Kroll的求解欧拉方程的有限体积法，推广到求解机翼机身流动问题，基本思想是使用保角变换、代数变换和椭圆方程变换混合方法生成机翼机身贴体网格。计算中使用有限体积法对欧拉方程进行空间离散，采用Runge－Kutta显式多步法求解关于时间的离散方程。在机翼机身表面上满足法向动量关系式。并采用了当地时间步长、隐式残值光顺和焓阻尼等技术加快收敛速度。本文方法具有准确、高效的特点，并可灵活应用到复杂流场计算中。

The finite volume technique used by Kroll to calculate Euler equations is developed in this paper to solve wing-body flow. A hybrid grid generation method composed of a conformal mapping procedure, a topology transformation using elliptic partial differential cquation and algebraic mapping is devclopcd to obtain body-fitted grids. In this paper,an explicit Runge- Kutta tinie-marching finite volume procedure, a combination of second-or forth-order dissipation, yariable-time steps and enthalpy damping is used. The code is effectiye and can be used for complex configuration conveniently.