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
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。
升力系数求解程序
- 计算特定飞机升力系数的程序
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
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。-Can generate a standard airfoil coordinates, and the airfoil at different angle of attack carried out under the lift coefficient and drag coefficient calculation software.
fanhuicang_6dof_rentry
- 根据返回舱GNC系统的任务,建立了适用于包括风在内的各种干扰作用下六自由度再入弹道仿真数学模型,为半实物仿真奠定了基础。提出了基于标准轨道的再入制导律,严格推导了再入段总升力方向控制中滚动通道姿态控制信号的形成,并给出了工程应用中简化的方法。开发了综合仿真软件 -err
Potential_Flow_Simulator
- 翼型在势流中的模拟，以求得其压力系数分布，升力系数等-Airfoil in potential flow in the simulation, with a view to obtaining the pressure coefficient distribution, the lift coefficient
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
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
aa
- 目录 1 阻力系数和升力系数的计算 1 2 俯仰力矩系数的计算 1 3 法向力系数对攻角导数的计算 1 4 俯仰阻尼力矩系数的计算 2 5 俯仰阻尼力矩系数的推导 2-aerodynamic coefficient
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
VLM
- 涡格法进行无人机的设计，升力系数，阻力系数，力矩系数等等，美过圣母大学的设计辅助软件-VLM
source123
- 基于源板块法的matlab模拟无升力圆柱绕流程序。空气动力学中的一个实验-Matlab source plate method based on simulation of flow around a cylinder without lift procedure. Aerodynamics of an experiment
euler
- 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
Fluent2D
- 飞机翼型的升力系数、阻力系数、压力中心等计算-Aircraft airfoil lift coefficient, drag coefficient, center of pressure computation
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
升力面
- 矩形水翼使用升力面方法进行计算的程序，matlab编程。包含均匀网格和余弦网格两种分格方法。(The rectangular hydrofoil is calculated using the lifting surface method, and the program is programmed by matlab. Two grid methods including uniform mesh and cosine mesh.)
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)
涡格法计算升力
- 利用涡格法计算对称机翼的升力，压心和焦点(Calculation of lift force, center of pressure and focus of symmetrical wing by vortex lattice method)