How Is Downforce Calculated on an Inclined Plane Using Aerodynamics?

AI Thread Summary
To calculate downforce on an inclined plane, key parameters include the surface area of the wing, the angle of attack, and wind speed. Additional inputs such as chord length and wingspan are necessary to accurately describe the wing's area distribution. A wing generates downforce by accelerating air downwards. For detailed lift and drag characteristics, researching "airfoil polar" can provide valuable insights. Understanding these factors is essential for accurate downforce calculations without practical experimentation.
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How would you go about working out the downforce of an inclined plane if you know the surface area of the wing, the angle of the wing and the windspeed, and obviosly without doing anything in terms of practical work? Any help would be greatly appreciated
 
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obviosly without doing anything in terms of practical work
A wing performs work on the air by accelerating it downwards.

You're also missing some inputs. The chord length (distance front to back) and the wing span (distance from tip to tip) are needed to describe how the wing area is distributed. The area alone isn't enough information.

I didn't have time to do a throurough search to answer your original question. Do a web search for

airfoil polar

and you should be able to sift through all the hits and find an answer for the lift and drag characteritics of a flat board.
 

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