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CharacteristicsAnalysisofLimited-Aspect-RatioWingB
- 涡格法计算有限展弦比机翼升力的程序，提供给研究机翼或螺旋桨的朋友-Characteristics Analysis of Limited-Aspect-Ratio Wing By Vortex-Lattice Method
vertex
- 该程序可用于计算无后缘后掠角的平板梯形翼在小攻角时升力与升力系数-This program can be used to calculate the plate without posterior trapezoidal wing sweep angle of attack in the small lift and lift coefficient
aerodynamic
- 气动特性计算，包括全机焦点，升力系数，极曲线，动导数等-Calculation of aerodynamic characteristics, including the focus of the whole machine, lift coefficient, polar curves, such as dynamic derivatives
SourceCode
- 采用升力线方法对螺旋桨进行性能计算并基于此进行螺旋桨的设计-Lifting line method of propeller performance calculation based on the design of the propeller
openprop.tar
- 升力线模型计算代码，将机翼表征为一个沿展向变化的涡线，通过尾涡计算诱导速度，实现计算的封闭。-Lifting line model code, the characterization of the wing along the exhibition to the change of the vortex line, trailing vortex induced velocity calculated closed.
Liftind-line
- Fortran版本的升力线模型源代码，目前只能计算平板机翼，尾涡模型采用的刚性螺旋尾涡。-Fortran version of the the lift line model source code can only calculate the flat-panel wing the rigid spiral trailing vortex wake model used.
avl3.31
- Drale编写的升力面模型，机翼表面被离散为涡格。与升力线模型相比，升力面模型更多的考虑了机翼的几何形状。-Lifting surface model Drale write the wing surface the discrete vortex lattice. Compared with the lifting line model, the lifting surface model consideration of the geometric shape of the wing.
flapping
- 使用非定常涡格法(UVLM)计算一种简单扑翼机的升力。对应文献Time Domain Modeling of Unsteady Aerodynamic Forces on a Flapping Airfoil -Eric Durand（MIT Master thesis）-Unsteady vortex lattice method (UVLM) a simple flapping wing machine lift. Corresponding literature Time Domain M
Take-off-and-landing-performance
- 飞行力学里计算最短起飞和着陆距离的程序，数据为各种马赫数下的升力和阻力系数-Take-off and landing performance
cxcy
- 黑鹰桨叶升力/阻力/力矩系数随迎角变化数据模型-The paddle lift/drag/moment coefficient different angles of attack data
aircraft-dynamics
- 计算飞行器升力系数，并绘制飞行器升力系数曲线。-calculate dynamic force for aircraft
wangge1
- 使用涡格法计算任意翼面的升力、阻力、俯仰力矩系数-CALCULATING wing vortex lattice method of using lift, drag, pitching moment coefficients. .
DLM
- 计算升力面非定常气动力的偶极子网格法MATLAB程序-Matlab functions to calculate unsteady aerodynamic pressures on a lifting surface using doublet lattice method.
mian
- 利用牛顿面元法计算飞行器的升力、阻力、俯仰力矩等。-Calculation of the aircraft lift, drag, pitching moment, etc. Newton panel method.
Caculation-for-NACA24012
- 程序包二维翼型，计算涡面元系数，画出翼型，压力系数，升力系数，并在来流速度为1的时候画出翼型上下表面的速度-Caculation for airfoil including
System-Identification
- 辨识升力系数以及阻力系数，运用递推最小二乘法及遗忘因子法最小二乘法进行系统辨识-Identify the lift coefficient and the drag coefficient, and use the recursive least squares method and the forgetting factor method least squares method to identify the system
Debug
- 计算机翼气动力的小程序方便使用，采用涡格法对机翼的升力进行计算，然后可以通过数据分析软件对结果进行拟合，从而得到机翼的升力线斜率。(The small program of the aerodynamic force of the computer is easy to use. The lift of the wing is calculated by the vortex lattice method, and then the results can be fitted by the da
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)
涡格法
- 采用涡格法估算低速飞机纵向气动特性，包括升力系数、阻力系数及俯仰力矩系数！(It's a great matlab program)
面元法空气动力学例程-matlab
- 面元法计算升力阻力等，空气动力学小算例，模型基于三段模型，使用方法见标注