– This must be modified for compressible flow.
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• Materials > Fluid > Air > ‘Create/Edit’
– For Density, select ‘Ideal Gas’ – For Viscosity, select ‘Sutherland’
– If not, use the drop down list to change!
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• Edit > Momentum Tab
– leave the defaห้องสมุดไป่ตู้lt settings which correspond to a stationary wall (relative to the fluid zone) with a no-slip condition.
WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Choose the solver and models
• Select the turbulence model to be used:
• Models > Viscous > Edit
• Choose k-omega (2-eqn) • Select SST, then OK
什么是赛车的空气动力学
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WS2: Transonic flow over NACA0012 Airfoil
关于例子
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Set Operating Pressure to 0 Pa
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WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Boundary Conditions
• Boundary Conditions > Zone > select ‘airfoil_lower’ • Check that the boundary zone type is set to ‘wall’
– In this case there is only one cell zone (with the default name of fluid) – In this case there is also only one material (air, which has been modified) – There can be multiple zones with user-specified names and multiple materials if required
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WS2: Transonic flow over NACA0012 Airfoil
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以下是例子的参考设置部分 例子来源于ANSYS教程
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WS2: Transonic flow over NACA0012 Airfoil
Therefore, with compressible flows, it is sometimes convenient to set to operating pressure to zero, and input/output ‘absolute’ pressures. This is simply a user preference. Other times it may be convenient to set a bulk flow operating pressure. The main thing to remember is that whatever operating pressure is set, this will be added to any gauge input pressures.
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• The maximum aspect ratio in this mesh is quite high, as will be examined shortly. • This is a result of placing the first grid point in the viscous sublayer close to the airfoil wall surface, for maximum accuracy in the turbulence model. • However, very long thin (stretched) cells can lead to problems, so we need to proceed with some checks.
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WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Define Materials
• Constant density air is the default fluid.
Case Setup: Define Materials
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Click ‘Change/Create’
Close the materials panel.
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WS2: Transonic flow over NACA0012 Airfoil
Ansys 空气动力学
兰常欣
Tips：
• 很多人想要视频里面的ppt做参考，我找了很久终于 找到了这个ppt。内容有所修改，大家选取自己需要 的内容看吧。 • ppt中Ansys的例子的ppt经过截取，同时模型无法提 供，请见谅。 • 视频地址如下： • /v_show/id_XNDQ0MzU1MzA 4.html
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– Models > Energy > Edit > Toggle ‘On’ – This is needed because the flow is compressible and temperature will be variable.
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– 例子图片如下，我没法附上模型。模型主要是个NACA0012的标准翼型，周围 包裹着质量很高的网格，细部图见下一页。
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WS2: Transonic flow over NACA0012 Airfoil
Examine the mesh
• Zoom in and examine the mesh.
• There is nothing else to assign to the fluid cell zone for this case
– Other tabs are enabled when the corresponding options are selected
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– Ideally, in high speed compressible flow modeling, these should be temperature dependent as well.
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WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Choose the solver and models
• Select the steady-state density-based solver:
– General > Solver > Type > select ‘Density-Based’ – General > Solver > Time > steady (default)
Case Setup: Assign Materials
• Check that ‘air’ is assigned to the cell zone ‘fluid’ • Cell Zone Conditions > Zone > ‘fluid’ > edit
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WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Operating Conditions
• Cell Zone Conditions > Operating Conditions
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– Note: can also be accessed from the boundary conditions panel
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WS2: Transonic flow over NACA0012 Airfoil
Case Setup: Choose the solver and models