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
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-James formats based on the CFD program to calculate the flow field and the NACA0012 airfoil lift drag coefficient. Fluent grid provided by the G
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 e
naca0012
- NACA0012翼型流场计算。结构化网格，AUSM格式。-NACA0012 airfoil flow field
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
center
- jamson中心格式求解naca0012翼型的绕流，计算精度较高-format solve naca0012 airfoil of jamson center around the flow calculation accuracy
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 cert
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
fortran-naca0012
- foutran语言，孤立翼型绕流程序,程序很长，需要耐心看，这是北航的作业程序-fortran language, isolated on the Flow around a program, the program is very long, you need to be patient, this is Northern operational procedures
1-C-grid
- 基于椭圆偏微分方程，针对NACA0012翼型生成C网格，生成最后的网格(C type mesh generation)
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)
O网格椭圆型生成法及求解势流方程
- 自动生成NACA0012翼型的网格，并在网格的基础上求解势流方程，fortran编译，可自改(O grid that mainly generates 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)
FLUENT动网格教程
- FLUENT动网格教程,以NACA0012翼型俯仰振荡实例进行讲解动网格的应用过程(FLUENT dynamic grid tutorial)
wangge
- 用MATLAB对NACA0012翼型进行了C型结构化网格划分(C-type structured meshing of NACA0012 airfoil is carried out with MATLAB)
椭圆型偏微分方程生成O型网格
- 基于椭圆型偏微分方程生成二维NACA0012翼型的O型网格并求解流场(Generation of O-grid of two-dimensional NACA0012 airfoil and solution of flow field based on elliptic partial differential equation)
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)