MAE: 4700 Wing Project

Description:

This page has helpful resources for the MAE 4700/5700 Wing Design Project.

Here is the .txt file used in the video below:

NACA_0012_Airfoil.txt

The video below shows you how to create the initial wing geometry in Ansys Discovery. 

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. Select the upper curve from the tree, select the Design tab and then “Pull” the curve to 15m. 
      3. Go into the Repair tab and box select the surface you have just created. “Merge Surfaces.”
      4. Repeat for the lower curve. 
      5. Pull the trailing edge profile to meet the length of the wings. 
   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

Reiterate with varying numbers of spars/ribs, varying locations, and different thicknesses. For varying thickness, look at setting up a parameter. This tutorial should help:

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