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03-21-2019
09:55 PM
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Hello. I try to calculate drag coefficient of a regular 3D wing. But in result I got value - 0.56. I think this is a very huge value for wing.
Wikipedia says that whole Cessna 182 have Cd = 0.027: https://en.wikipedia.org/wiki/Drag_coefficient#Aircraft
For calculating I use tutorial and formula published here https://knowledge.autodesk.com/support/cfd/learn-explore/caas/simplecontent/content/calculating-the-...
My parameters for formula:
Force by direction 380 Newton;
Velocity 50 m/s
Cross sectional area 0.45 m2
Air density 1.2
Please, review my model located here https://drive.google.com/file/d/1uwAfzZR1i6F6BaviWUa09O--xCsmIG-U/view?usp=sharing and tell me what I am doing wrong.
Solved! Go to Solution.
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