fluent 验证案例17:Transonic Flow over an RAE 2822 Airfoil 跨音速流动在rae2822翼型 流过一个rae2822翼型在自由流马赫数0.73。迎角为2.79°。流场是二维的、可压缩的(跨音速)和湍流的。 使用了基于密度的求解器的隐式公式。使用SST k-ω湍流模式来解释湍流效应。 1、几何建模,网格划分 这里使用胡坤老师的case...
% Marker(s) of the surface to be plotted or designed MARKER_PLOTTING= ( AIRFOIL ) % % Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING= ( AIRFOIL ) (5)数值求解通用参数 % --- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---% % %...
% Navier-Stokes wall boundary marker(s) (NONE = no marker) MARKER_HEATFLUX= ( AIRFOIL, 0.0 ) % % Farfield boundary marker(s) (NONE = no marker) MARKER_FAR= ( FARFIELD ) % % Marker(s) of the surface to be plotted or designed MARKER_PLOTTING= ( AIRFOIL ) % % Marker(s) of th...
Reynolds averaged Na- vier-Stokes flow computation of RAE2822 airfoil using gas-kinetic BGK scheme [A] // IMECS 2009 [C]. Hong Kong: 2179~2183Ong J. Chit, Ashraf A. Omar and C. V. Rorst, "Reynolds Averaged Navier-Stokes Flow Computation of RAE2822 Airfoil Using Gas-kinetic BGK Scheme...
An experimental study of pressure distributions over RAE2822 airfoil in the two-dimensional test section 0.8×0.4 meter of a transonic wind tunnel which is the first pressruized continuous wind tunnel in China is presented. This paper in order to further study the influence of the dynamic of co...
(b) 局部变形(b) Local mesh deformation图4 RAE2822翼型网格变形示意图Fig.4 Diagram of RAE2822 airfoil mesh deformation 基于FFD技术对翼型进行参数化建模,在上表面和下表面分别选取6个控制点,具体控制点的分布如表2所示。由于RAE2822是非对称翼型,所以上下表面不采用统一变形。首先将翼型的顶点和尾部汇合点固定...
The ground effect would induce the upfront separation of boundary layer on the airfoil. In study of the ground boundary condition and compressibility effect, these factors all show significant impact on the aerodynamic characteristics of RAE2822 in ground effect, which should be considered in ...
FFD (free-form deformation) technique was applied to achieve the parameterization of RAE2822 transonic airfoil. Then the method of DoE (design of experiment) was used to obtain the sample values of design parameters by CFD (computational fluid dynamics) numerical simulation. Lastly, the optimization...
Swept RAE2822 wingSwept wing is widely used in civil aircraft,whose airfoil is chosen,designed and optimized to increase the cruise speed and decrease the drag coefficient.The parameters of swept wing,such as sweep angle and angle of attack,are determined according to the cruise lift coefficient ...
viscosity/ Navier-Stokes flow computationNavier-Stokes flow solverfinite-volume cell-centered explicit Runge-Kutta time stepping schemeTransonic flow over the RAE2822 airfoil has been solved for flow coditions corresponding to the AGARD test case 10. An extensively tested steady Navier-Stokes flow ...