STAR CCM跨音速流动,嵌套网格,变攻角2D

发布网友 发布时间：2023-01-05 16:15

我来回答

共1个回答

热心网友 时间：2023-10-16 04:50

文件地址为安装目录下的doc/startutorialsdata/compressibleFlow/data/airfoil_oversetParts.sim

另存到一个合适的地方

You create two Automated Mesh Operations to represent the Background and Overset regions.
The Automated Mesh Operations contain the same meshers, but use different mesh settings. It is important that, in the overlapping zone, which is defined by the Overset Boundary, mesh cells are of a comparable size in both meshes.
步骤：

（以下7/8步可以直接拉到后面的图示看）

With both Automated Mesh Operations for the background mesh and the overset mesh set up, you generate the volume mesh. You then convert the mesh from 3D to 2D to simplify the solution.

To generate the mesh:

1.To build the volume mesh, click the Generate Volume Mesh button in the toolbar. This process can take a few minutes.
点击工具栏中的生成体网格按钮

2.To view the mesh, create a mesh scene.
生成一个网格场景以查看网格

3.Zoom in on the Overset boundary to compare the cell size of the overset mesh to the background mesh at this boundary.
中键缩放，右键平移查看结果

You can convert the mesh from 3D to 2D to simplify the solution.
将3D网格转换到2D网格

Rotate the Overset region to correspond to a 2.54° angle of attack of the airfoil.
将嵌套网格区域旋转到2.54°攻角。

The steps presented here demonstrate how using overset meshes allows you to change the relative position of bodies without the need to generate a mesh.

Overset regions are coupled to the background region using the Overset Mesh interface.
Normally, this interface can be created before generating the background and overset meshes. To activate this interface feature, you must create a physics continuum. Current implementation requires that the background and overset regions use the same physics continuum. In this tutorial, you are creating the Overset Mesh interface after converting the mesh to 2D as this step deletes all previously created interfaces.
To create the interface:

An Overset Mesh 1node appears under the Interfaces. Use the default Distance Weighted Interpolation Optionfor the mesh coupling.

When you initialize the Overset Mesh interface, STAR-CCM+ chooses acceptor cells on the overset region. Cells in the background region that are overlapped by the overset region are deactivated.

Display cell status in a scalar scene.
To analyze the mesh before running the simulation, initialize the Overset Mesh interface:

Notice that the background mesh within the airfoil part has been removed in Mesh Scene 1.

Analyze the overset mesh using the Overset Cell Status field function.

First look at the cell status in the overset region.

Acceptor cells outline the overset region in blue.

Models define the spatial and temporal solution methods and the physical properties of the flow.
In this example, the flow is steady, turbulent, and compressible. Use the default Spalart-Allmaras Turbulencemodel and the ideal gasmodel. The analysis also uses the coupled solver, which is recommended for all supersonic and transonic compressible flows.
By default, a continuum called Physics 1 is created when the three-dimensional mesh is generated and a Physics 1 2D continuum is created when the mesh is converted to two-dimensional. You can delete the Physics 1 continuum, as only one is used in this simulation.

Set the Reynolds numberto 6.5e6, changing the dynamic viscosity
Use the following steps:

As in the Transonic Flow tutorial, initialize the velocity field to 250.0 m/s.

The default values for the remaining initial conditions are suitable for this tutorial.

Set the conditions at the boundaries of the airfoil and the domain.

The geometry used for this tutorial has only two boundaries for the physics:

Set the freestream conditions on the outer perimeter of the Background region.

1.Edit the Regions > Background 2D > Boundaries > Outside > Physics Valuesnode and set the following properties:
双击设置区域>Background 2D>边界>Outside>物理值

All other conditions for the freestream boundary and the default wall are suitable for this problem.

The simplicity of this problem allows a rapidly converging solution to be obtained using a larger Courant number.
In problems involving more complex geometries or physics, attempting to shorten the run time in this way may cause the solution to diverge.
To increase the Courant number:

View the Mach number profile ring the run to monitor the supersonic flow region above the airfoil.

Use the following steps:

1.Create a scalar scene.
A new Scalar Scenedisplay appears.
右击并选择生成场景>新场景>标量

2.Right-click the scalar barat the bottom of the display and select Mach Number > Lab Reference Framefrom the pop-up menu.

3.Initialize the run by clicking Initialize Solutionin the toolbar, then use the middle mouse button to zoom in on the airfoil in the center of the scalar scene.
在工具栏中点击初始化求解

4.To change the style of the Mach number contours, select the Scalar Scene 2 > Displayers > Scalar 1node and set Contour Styleto Smooth Filled.
选择场景>标量场景2>标量1，将轮廓样式设置为平滑填充

To determine when the problem has converged, plot the lift and drag coefficients.
Use the following steps:

右击报告选择新报告>力系数