点击按钮Output Control弹出设置对话框 如下图所示定义监测变量Lift Coef,force_x_Coord 1()@airfoil * 2 / (massFlowAve(Density)@inlet*(massFlowAve(Velocity)@inlet)^2*0.6 [m]* 1[m]) 如下图所示定义监测变量Drag Coef,force_z_Coord 1()@airfoil * 2 / (massFlowAve(Density)@inlet * (massFlowA...
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An experimental study of static and dynamic pressure distributions over a NACA 0012 airfoil in the two-dimensional test section 0.8 × 0.4-meter of a transonic wind tunnel is presented. Tests are conducted at freestream Mach numbers from 0.35 to 0.89, and angle of attack between -2.0° and ...
Investigation of NACA 0012 Airfoil Periodic Flows in a Transonic Wind Tunnel - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition (AIAA) 来自 AIAA 喜欢 0 阅读量: 62 收藏 报错 分享 全部来源 求助全文 AIAA ...
First, experimental and numerical methods used to investigate the flow and lift force of a NACA0012 airfoil in the low Reynolds number range Re∈[50,000:140,000] are described. Second, predictions from low and high-fidelity simulations are compared with experimental data for the lowest Reynolds...
This research paper presents the design and analysis of a NACA 0012 airfoil with a circular dent of 30 mm depth on its upper surface. The objective of this study is to investigate the effect of the dent on the airfoil's aerodynamic performance. The airfoil's geometry was modeled using a ...
The NACA 0012 airfoil is widely used. The simple geometry and the large amount of wind tunnel data provide an excellent 2D validation case. For this case I use the Spalart-Allmaras turbulence model. Mesh The mesh is a 30,000 cell structured C-grid. The chord length is 1 m. The width ...
Effect of Full-Chord Porosity on Aerodynamic Characteristics of the NACA 0012 Airfoil herein was conducted in the Langley 8-Foot Transonic Pressure Tunnel (ref. 10) with a two-dimensional model that incorporated the NACA 0012 airfoil ... Mineck, R. E,Hartwich, P. M - NASA Langley Technical...
Separation control on NACA 0012 airfoil using momentum and wall-normal vorticity injection We numerically investigate the inuence of momentum and wall-normal vorticity injection in separation control of flow over a spanwise periodic NACA 0012 airfoil at a Reynolds number of 23,000. Large-eddy simulat...
The simulation results obtained for the NACA 0012 airfoil show that the combination of the second order slip/jump boundary conditions gives suitable agreements with DSMC for surface gas temperature and drag coefficients in comparison with those of the first order conditions. However, the results...