搜索资源列表
Euler
- 基于James格式的CFD程序,计算NACA0012翼型流场和升力阻力系数.网格由Fluent提供的Gmbit生成,计算结果可以通过Tecplot观看
ausm-euler0012
- this fortran code can be used for analyse Inviscid flow over naca0012 airfoil with C_type grid. this code is developed by AUSM+ method.
naca0012
- NACA0012翼型流场计算。结构化网格，AUSM格式。-NACA0012 airfoil flow field
euler
- naca0012 源程序 里面附有升力阻力阻力系数的计算结果，仅供参考-Naca0012 inside source program with lift resistance drag coefficient of the calculation results, only supplies the reference
src
- 逆风格式欧拉方程求解naca0012二维翼型流场程序，内附网格文件和输入参数。-Wind Euler equations naca0012 format two-dimensional airfoil flow field procedures, containing the grid files and input parameters.
EULERAUSM
- 基于ausm格式的欧拉方程求解程序，附带有naca0012的翼型数据，是学习计算流体力学的好例程，费尽心思编写的，注释多多，便于阅读-Ausm format based on the Euler equation procedures, comes with naca0012 the airfoil data, computational fluid dynamics is a good learning routines, the effort to prepare, notes a lot
C-type-gridgeneration-for-naca0012
- this code can be used to develop C-type grid generaton for naca 0012 airfoil. by import the airfoil dots with manner of the code, you can develop c_type grid for any airfoil.
fortran-files
- 文件1.f90：生成翼型naca0012的椭圆网格，并计算流场，给出壁面压力分布 文件2.f90：maccormack方法解一维burger s方程 文件3.f90：解一维laval管流动，其进出口均为亚音速，喉道后部有激波-File 1.f90: generate the airfoil naca0012 elliptical rotary cell, and calculate the flow field, given the wall pressure distributio
Euler_solver
- 基于有限体积法的naca0012翼型的无粘绕流计算-Calculation of airfoils based on the finite volume method naca0012 inviscid flow around
naca0012
- 采用椭圆型偏微分方程生成的O网格，简单实用 适合初步学习网格生成的代码， 仔细看看代码的机构 会学到实用的技巧-naca0012 airfoil with o-grid based on the elliptical partial differential equations
NACA0012-Ogrid
- NACA0012翼型O网格生成；速度势方程解流场-NACA0012 airfoil O mesh generation flow field velocity potential equation
naca0012-24-15
- 用于分析高雷诺数naca0012翼型和圆柱绕流，基本可用，但数值误差大，可通过修该某些参数缩小误差-For the analysis of high Reynolds number flow around a cylinder naca0012 airfoils and basic available, but the numerical error, the error can be reduced by modifying certain parameters the
naca0012-24
- 用于LBM-LES的大涡模拟，分析高雷诺数naca0012，7度攻角，有涡出现-For large-eddy simulation LBM-LES analyze high Reynolds naca0012, 7 degree angle of attack, there appeared vortex
naca0012
- 2D Naca0012 Airfoil Mesh With Gambit
NACA0012
- 用来生成翼型NACA0012的计算网格，此网格可用于后续计算。程序数据在附件里。(A computational mesh used to generate airfoil NACA0012)
naca0012翼型网格生成
- C语言生成C型网格，求解拉普拉斯方程生成网格并计算压力系数(Solve the Laplace equation to generate the grid and calculate the pressure coefficient)
NACA0012
- 此文件为naca0012翼型的msh格式(msh format of NACA0012 airfoil)
NACA0012
- NACA0012翼型的网格生成以及零攻角绕流流场计算(Mesh generation of NACA0012 airfoil and calculation of flow field around zero angle of attack)
ausm
- 利用AUSM格式来求解欧拉方程,对NACA0012翼型进行流场求解,生成结构化网格(solve euler equation by the method of AUSM,and grid generation is done with structed grid)
naca0012
- 有限体积法,通过有限体积法求解naca0012流场，通过有限体积法求解naca0012流场(finite volume method)