This example is taken from Cornell University’s ANSYS AIM Learning Modules

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.

Geometry & Mesh

Download the file here

In this video, you will learn how to import the geometry, perform required geometry operations in Discovery AIM and how to generate mesh in the computational fluid domain.

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Physics Setup

In this video, you will learn how to specify fluid flow conditions.

Results Evaluation

In this video, you will learn how to evaluate velocity vectors, Total Pressure and Temperature contours in the flow domain.

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Verification

In order to verify that the simulation is accurate, it must be compared to a study that is similar in nature. We will compare the AIM results with results from Stanford University’s Aerospace Design Lab. In that study, users were expected to become familiar with performing an optimal space design in a 2D space. The airfoil used was also the NACA 0012, which makes this a perfect example to compare ours to. Below is the pressure contour that was plotted as a result of the Stanford tutorial, which can be directly compared to the pressure contour found in the previous section.

References

Copeland, Sean and Economon, Thomas. “Quick Start Tutorial – SU2 – ADL Software Documentation.” Aerospace Design Lab. Stanford University, 1 July 2014. Web. 7 August 2017.