搜索资源列表
NACA
- 计算NACA4位翼型的程序,在E盘naca文件夹下生成翼型数据,保存为.txt格式-calculated NACA4 - airfoil procedures, the E-folder NACA airfoil data generation, preservation of. Txt format
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
pablo
- 一个可以生成标准翼型坐标，并对翼型在不同攻角下进行升力系数及阻力系数计算的软件。
pyxfoil
- 二维翼型坐标生成与气动力计算
NACA
- 计算NACA4位翼型的程序,在E盘naca文件夹下生成翼型数据,保存为.txt格式-calculated NACA4- airfoil procedures, the E-folder NACA airfoil data generation, preservation of. Txt format
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
aiefoilconclution
- 已知实验测得的翼型的压力分布和翼型数据，计算其升力系数和阻力阻力-Known experimental measured airfoil pressure distribution and airfoil data to calculate the lift coefficient and drag resistance
P_Q
- 2MW风机的最大功率跟踪(根据叶片翼型计算)-The maximum power point tracking of the 2MW wind turbine according to the blade airfoil
TTM方法生成翼型网格MATLAB程序
- 计算流体力学小程序：使用TTM方法生成机翼翼型网格(generate the wing grid with TTM method)
Laplace
- 求解椭圆型方程生成二维翼型网格，并采用逐线松弛迭代技术求解了二维翼型绕流，这是CFD计算中的典型例子，是cfd初学者的很好的学习例子。(Solving elliptic equations, generating two-dimensional airfoil mesh, and using line relaxation iterative technique to solve the two-dimensional airfoil
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)
javafoil
- 设计飞机翼型，可以自己设计飞机翼型点，计算压力分布(design aircraft airfoil)
qhyx64
- 计算一般翼型的升力系数，速度和攻角可在程序中自行调整(Calculation of lift coefficient of general airfoil)
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)
Construct2D_2.1.3
- 翼型计算的2D网格生成代码，学习和研究抛物和椭圆型网格生成算法(2D grid generation for computational fluid dynamics.Hyperbolic and elliptic grid generation available)
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)
Vortex2D
- 输入naca四位数翼型，和环境参数，可以计算得到压力分布和升力系数(Pressure distribution and lift coefficient can be calculated by inputting NACA four-digit airfoil and environmental parameters.)
DIY-Wind-Turbine-Analyzer-master
- 用叶素动量理论来求解维尔森方法中，翼型气动性能，轴向与切向诱导因子的计算程序(Calculation of airfoil induction factor)
10+-15
- fluent计算翼型做正弦型俯仰运动的udf，运动幅度10+-15°(udf for fluent calculating a pitching wing)