用空间推进算法模拟高超声速进气道流场

Numerical Simulation of Hypersonic Inlet Flows Using a Parabolized Navier-Stokes Algorithm

在有限体积法框架下，采用空间推进算法SSPNS（Single-Sweep Parabolized Navier-Stokes Algorithm）求解抛物化NS方程（即PNS方程），在流向采用LU—SGS隐式积分，而横向无粘和粘性通量则分别采用AUSM系列格式和中心格式计算。用该方法对1个二维高超声速进气道和2个三维高超声速进气道流场进行了数值模拟，得到的流场波系结构、壁面压力及传热系数分布与文献中相关数值解和实验数据基本一致，表明SSPNS法能够准确地模拟超燃冲发动机进气道内的高超声速流动。对比研究表明，SSPNS法与求解FNS（Full Navier＼lStokes Equations）方程的传统时间迭代法相比，二者计算精度相当，而SSPNS计算速度快1～2个量级，存储量至少低1个量级。本文的研究为CFD在超燃冲压发动机部件及一体化优化设计中的集成，以及大型高超声速工程流动的高效计算，打下了良好的基础。

An impheit finite volume upwind space-marching CFD solver, i.e. Single-Sweep Parabolized Navier-Stokes Algorithm （SSPNS）, is developed by integrating the PNS equations with LU-SGS method in the streamwise direction. The transverse inviscid and viscous numerical fluxes are calculated with AUSM-family upwind schemes and central scheme, respectively. Several hypersonic inlet flows, including 1 2D and 2 3D cases, are computed by SSPNS codes. Results of the 2D inlet, including flow structure, wall pressure distribution and heat transfer coefficients, are in good agreement with those of NASA＇ s UPS and BeamWarming PNS codes. Wall pressure distributions of the 3D side-compression inlet also agree well with experimental and SCRAMIN numerical results by Holland et al. By comparison with the FNS flow solvers, the SSPNS codes show at least 1 - 2 order of magnitude speed faster and 1 order of magnitude of storage saving in the 3D top-side-compression hypersonic inlet flow simulation. All these numerical results prove that SSPNS is a highly efficient and accurate algorithm for steady supersonic/hypersonlc flows, especially for 3D cases, and it is suitable to be integrated into the aerodynamic optimization design process of scramjet and its components.