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Description: 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
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Size: 645021 |
Author: 凌维安 |
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Description: 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 Gmbit generated, calculated results can Tecplot Views
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Size: 876544 |
Author: 凌维安 |
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Description: 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 of easy-to-read
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Size: 460800 |
Author: 袁振伟 |
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Description: NACA0012翼型流场计算。结构化网格，AUSM格式。-NACA0012 airfoil flow field
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Size: 598016 |
Author: newanda |
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Description: this fortran code can be used for analyse Inviscid flow over naca0012 airfoil with C_type grid. this code is developed by AUSM+ method.
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Size: 3072 |
Author: kiarash |
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Description: 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.
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Size: 3072 |
Author: kiarash |
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Description: 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.
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Size: 207872 |
Author: |
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Description: 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
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Size: 60416 |
Author: 仇建新 |
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Description: 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 distribution file 2.f90: maccormack method to solve the burger' s equation, one-dimensional file 3.f90: solution of one-dimensional laval tube flow, its progress exports are subsonic, the back of the throat have shock
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Size: 5120 |
Author: 李盈盈 |
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Description: 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
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Size: 1024 |
Author: chanzhaolin |
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Description: 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
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Size: 3072 |
Author: 周一 |
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Description: 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
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Size: 3072 |
Author: 宋明健 |
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Description: 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
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Size: 3072 |
Author: 宋明健 |
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Description: 2D Naca0012 Airfoil Mesh With Gambit
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Size: 840704 |
Author: majidmanz
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Description: 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)
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Size: 30720 |
Author: Johnsonnnn
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Description: 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)
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Size: 23552 |
Author: hetan
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Description: 此文件为naca0012翼型的msh格式(msh format of NACA0012 airfoil)
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Size: 553984 |
Author: zlxly |
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Description: 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)
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Size: 3072 |
Author: Ericzeta |
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Description: 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)
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Size: 3072 |
Author: 212121dear |
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Description: 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)
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Size: 19456 |
Author: mo1415 |
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