超音进气道流场的数值计算

用Jameson的有限体积法，对某型号飞机在不同飞行状态下的进气道流场进行了数值模拟。求解的控制方程为三维非定常N-S方程。在对流项的计算上用二阶中心差分有限体积法，粘性项的计算则采用作者在［1］中发表的一种有限体积框架下的新的离散化技术，时间方向用多步Runge-Kutta方法进行推进，以增大CFL条件数。湍流模型则采用Baldwin-Lomax代数模型。求解过程中还采用了当地时间步长，隐式残量平均、人工粘性等加速收敛技巧。最后给出了各种飞行状态下进气逼出口截面的平均总压恢复与总压畸变，得出了比较满意的结果。

Numerical Simulations of 3-D Supersonic Inlet Flowfields

In this paper,three-dimensional Supersonic inlet flowfields have been calculated.The governing equations are nonsteady compressible Navier-Stokes equations. The discretization was Jameson's Runge-Kutta finite volume method. Modified Baldwin-Lomax algebraic eddyviscosity turbulent model and the wall function law were used. A new viscous terms discretization in the frame of finite volume method was adopted. For convergence acceleration,local time stepping,implicit residual average and artificial dissipation techniques were also used.A aircraft inlet flowfields of several flight states were calculated. The mean total pressure recovery and total pressure distortion across the engine face were obtained. These results were compared with experiment data and were proved to be satisfactory.