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weno-codes
- weno code, 计算经典的双马赫数反射的问题-WENO code double mach refelct
w
- CFD经典算例：双马赫反射，采用五阶WENO格式，可作为测试算例，激波分辨率-CFD classic example: the double Mach reflection，Fifth-order WENO scheme can be used as the test example。Shock resolution
WENOPLFPRK
- 利用5阶有限差分weno结合LF流通量分裂，3阶runge-kutta求解双马赫反射、黎曼问题、界面不稳定性问题-Order finite difference weno combination of LF liquidity split third-order runge-kutta to solve the double-Mach reflection, the Riemann problem for interface instability
k_pohlhausen
- 已知翼型坐标及其各点的马赫数分布用波豪森近似方法求解层流附面层厚度-The known airfoil coordinates of its point of Mach number distribution wave the Stockhausen approximation method for solving laminar flow boundary layer thickness
xie-shock
- 计算二维斜激波各个变量之间的关系，输入波前马赫数，sita,beta之中的任何两个，可以求出压力，密度，马赫数等波后量与波前量的比值-Relationship between the variables of the calculation of two-dimensional oblique shock, out of any two of the Mach number, sita, beta, the input wavefront, which can be determined pre
SciDAC-June-2005.pdf
- This is a good descr iption of computational effort to simulate turbulent reacitng flows at high mach nunbers and is about 7 years old.
CFD
- 这是一个求解NACA0012翼型在不同马赫数与攻角下的流场的Fortran源代码。计算格式采用了原始AUSM、AUSMDV以及AUSM+格式。为了提高计算精度，使用了不同限制器的MUSCL插值。-This is a Fortran source code for solving the flow field around the NACA0012 airfoil at different Mach numbers and angles of attack. The scheme of AUSM,
zulixishu
- 使用插值法计算阻力系数，给出不同马赫数下的阻力系数，然后对给定马赫数进行插值-Drag coefficient is calculated using the interpolation method, the drag coefficient is given under different Mach number, and then interpolate a given Mach
Task3B
- 安德森的空气动力学大作业。计算扩压器中背压改变引起的流动中马赫数的变化。和激波位置的移动。matlab编。-Anderson s book. Aerodynamic.When back pressure changes, Mach number changes.
lax3
- 一个使用LAX格式的欧拉方程求解激波管的FORTRAN语言程序，结果可以得到密度、速度、压力、马赫数的分布。-A solution of euler equations using LAX format shock tube FORTRAN program, the result can get the distribution of density, velocity, pressure and Mach number.