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  • Compressible Flow Over an Airfoil - Validation

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By comparing this to the Stanford’s pressure contour, it is easy to see that they are similar.  Also, the numerical minimum and maximum values are significantly close, by less than 10%.

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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.

 


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