Compressible Flow Over an Airfoil

Created using ANSYS 18.1

Problem Specification

A wing with a NACA 0012 airfoil section has a chord of 1 meter, a span of 1 meter, and a thickness of 0.01 meter. The wing is made of Aluminum 6061-T6. If air moves at 987.84 km/hour around the airfoil, find the velocity vectors of compressible flow over the airfoil.

Go to Step 1: Start-Up

Go to all ANSYS AIM Learning Modules

  • No labels