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Description:

This page has helpful resources for the Fall MAE 4700/5700 Wing Project which includes a demo video with no sound, a project outline of steps in ANSYS, and an FAQ that will be updated as questions come in.

Note:

Please note that the video was created using Apps on Demand. The ANSYS license on AoD does not support the number of nodes that was used in the video. To receive your solution, please remotely connect to a Swanson Lab computer to run your simulation. If you find that you created the everything except for the mesh in AoD, simply save (archive) your project and transfer it over. The best method for doing this that I have found is to email yourself and open the file on the Swanson Lab computer.

Directions for connecting to the Swanson Lab computers can be found here:

https://confluence.cornell.edu/x/WJ0MF

Also, please note that this video is a demonstration of me creating a simple geometry. There is no sound in the video. Creating the geometry/solution can be achieved in many different methods. This video is simply an example.

 Design Project.

Here is the .txt file that was used in this tutorial:the video below:

View filenameNACA_0012_Airfoil_4Meters.txtheight250

Mesh: The video below has a mesh size that is much smaller than you need. Realistically, an element size of around 1 meter is a good starting size

...

at the link below shows you how to create the initial wing geometry in Ansys Discovery. 

<iframe width="560" height="315" src="https://www.youtube.com/embed/3UMF_X4qfs83XBw_VRNLXU?si=wE9OlyqJSnPHxCPm" title="YouTube video player" frameborder="0" allow="accelerometer; autoplay; clipboard-write; encrypted-media; gyroscope; picture-in-picture; web-share" referrerpolicy="strict-origin-when-cross-origin" allowfullscreen></iframe>

Summary of Steps:

1. Static Structural

2. Eng. Data

1. 1. Create New Material: Aluminum 2024-T36
   2. Linear Elastic>Isotropic Elasticity
      1. Add appropriate material properties
   3. Strength>Tensile Yield Strength
      1. Add appropriate material properties

3. Geometry

1. 1. New SpaceClaim Geometry
   2. Change units
      1. File>SpaceClaim Options>Units
      2. Change length to meters
      3. Change minor grid spacing to .1 m
   3. Import Wing
      1. Sketch New Sketch Plane
      2. XY plane
      3. Assembly>File
         1. Choose All Files
         2. Open NACA_0012_Airfoil_4Meters.txt
      4. Close trailing edge
      5. Return to 3D Mode
   4. Pull Wing
      1. Design>Edit>Pull
      2. Pull all three surfaces (Top half of wing, bottom half of wing, trailing edge) 15 meters
   5. Create Ribs and Spars
      1. Create Plane Along Z Axis
         1. Design>Create>Plane
         2. Move plane to designated position (Design>Edit>Move)
      2. Design>Mode>Sketch Mode
         1. Click on new plane
         2. Design>Sketch>Project to Sketch
            1. Click on the curves that represent the top/bottom of the airfoil
            2. Click on the trailing edge
         3. Click on Fill
            1. Select all three surfaces again
   6. Repeat process for each rib
   7. Repeat process for each spar but along the X axis
   8. Share Topology
      1. Click on Design1
      2. Properties>Analysis
      3. Share topology: Share

4. Model Setup

1. 1. Add a thickness to your surfaces and change the material assignment
   2. Create named sections (optional, just good practice)
      1. Wing surface
      2. Spars
      3. Ribs
      4. Wing Tip
   3. Mesh
      1. Face Sizing
         1. Geometry should be the entire body
         2. Confirm quadrilaterals Is selected
      2. Sizing
         1. Select body again
         2. Choose sizing
         3. Behavior: Hard
   4. Add fixed support
      1. Extend to limits
   5. Add pressure loads
      1. Make sure the load is Normal to Surface
      2. Add pressure loads to top and bottom surface
      3. Note gauge pressure

5. Solve Model

1. 1. Click Solve

6. Solution

1. 1. Add Total Deformation
   2. Add Equivalent (von-Misses)

7. Reiteration

The video at the link below shows you how to set up the initial wing analysis in Ansys Mechanical. 

<iframe width="560" height="315" src="https://www.youtube.com/embed/xx65AsQU2Ic?si=ngVAc1fuQRVFlWWh" title="YouTube video player" frameborder="0" allow="accelerometer; autoplay; clipboard-write; encrypted-media; gyroscope; picture-in-picture; web-share" referrerpolicy="strict-origin-when-cross-origin" allowfullscreen></iframe>

Reiterate with varying numbers of spars/ribs, varying locations, and different thicknesses. For varying optimizing thickness, look at setting up a parameteryou can use Response Surface Optimization. This tutorial should help:

https://confluence.cornell.edu/display/SIMULATION/ANSYS+-+Plate+With+a+Hole+Optimization