搜索资源列表
pablo
- 面元法计算机翼气动参数，有nasa上百个翼型库文件，可以手动加载，进行翼型设计时可以选择和profile配合使用-pablo
aerodynamics_Analyzer
- 这是一个小，但是非常有用的工具，用于分析飞行器的翼型。可以分析和比较飞机机翼几何特征，很快的绘制出机翼。包括：前缘半径、翼弦、厚度、中弧线、弯度和尾缘厚度等，这些参数直接影响翼型的气动性能。 - Airfoil Analyzer Small but essential tool for all Aerospace Engineers and Scientists.
Airfoil_Analyzer
- 翼型分析代码，计算分析机翼外流场。先关参数的分析，辅助设计。-Airfoil analysis code
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.
TheNURBSBook
- 工程界几何模型参数化用到的NURBS曲线生成的理论和相关源代码。可用以翼型参数化、船舶外形参数化等-the theory of NURBS curve generation and the related source code for Engineering of geometric model parameterization . Airfoil parameterization and ship shape parameterization can be used
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
CST_airfoil_fitting
- 一个拟合CST曲线的程序，用来做翼型优化使用（也可以用到其它曲线拟合上）。 首先读入一个翼型数据，反求这个翼型的6*2个控制参数。通过这修改这个12个控制参数（其中的任意几个），来达到生成新的翼型的目的。(使用了NASA0714翼型作为例子 )-it is a code for airfoil curves fitting, which based on CST formula.Firstly, the program read a airfoil data,then the program
par
- 基于Bezier曲线的翼型参数化，相比基于样条曲线的翼型参数化方法，该方法具有较好的鲁棒性-airfoil parameterization method base on Bezier Curve,it is more stable than the parameterization method base on Spline
zuobiaobianhuan
- 这个程序主要是把二维翼型坐标变换成三维翼型坐标，通过翼型位置-弦长-扭角等参数得到三维翼型坐标，完成后面的三维建模-This program is mainly two-dimensional airfoil coordinate into the three-dimensional coordinates of the airfoil, the airfoil by position- to give the three-dimensional coordinates of the airfo
DFFD
- 直接FFD（DFFD）几何参数化方法，可以对二维翼型实现参数化，实现网格变形(DFFD parameterization technique, used to deform the 2D airfoil)
ypjs
- 基于profile中翼型的风力机叶片设计程序，可由功率计算风机直径等参数(Based on the airfoil design program of profile, the parameters of fan diameter can be calculated by power.)
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.)
xfoil m files
- matlab和xfoil之间的接口，直接通过运行matlab运行xfoil，输入翼型坐标数据得到翼型的气动参数。(The interface between MATLAB and xfoil can directly run xfoil by running matlab, and the aerodynamic parameters of airfoil can be obtained by inputting airfoil coordinate data.)
shape parameterization mothods
- 多学科优化参数化建模MATLAB程序，对翼型进行参数化建模(MATLAB Program for Parametric Modeling of Multidisciplinary Optimization)