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| Modal Analysis of a Wing - Panel |
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| Modal Analysis of a Wing - Panel |
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Modal Analysis of a Wing
Created using ANSYS 13.0
Problem Specification
A wing with a NACA 0012 airfoil section is supported such that one end is fixed and the other end is free. The wing has a chord of 1 meter, a span of 5 meters, and a thickness of 0.01 meters. The wing is Aluminum 6061-T6. Find the first 6 modes of vibration of the airfoil using ANSYS Workbench.
Go to Step 1: Pre-Analysis & Start-Up
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