Hello Everyone ,
I am running a 3D simulation of an airfoil . The results I am getting for drag or lower than that of experimental results . I wanted to know could I calculate the value of lift induced drag from drag polar ?
yes you can
Dear Sultan
My modest contribution:
1. file:///C:/Users/dregodic/Downloads/GradTeam2ndPlace.pdf
2. http://www.stengel.mycpanel.princeton.edu/MAE331Lecture4.pdf
3. https://aerotoolbox.net/drag-polar/
4.https://www.nordian.net/REPOSITORY/117_jaa_principles_of_flight_demo.pdf
5. http://www.iaa.ncku.edu.tw/~aeromems/Aerodynamics/Ch5.pdf
6. http://www.iaa.ncku.edu.tw/~aeromems/Aerodynamics/Ch5.pdf
With respect
Dušan Regodić Thank you so much
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