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How would I calculate the lift force as a function of angle of attack for a revolved NACA 0009 3D body (incompressible flow)? I have data for CL vs. AoA for the 2D airfoil, but how would I use this to calculate the lift force on the body?

In the lift equation, I'm specifically wondering what to use for CL and S. (dynamic pressure is straightforward)

Would I just use planform area of the 3D body for S and 3D, incompressible lift coefficient for CL? Where AR is the aspect ratio of the body. See below for 3D adjusted equations.

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  • $\begingroup$ It looks like an airship 😉 maybe this report NACA can help you. Anyway do not expect it to generate lot of lift: I would say an order of magnitude less than the relevant airfoil. And for sure you cannot use the equation you posted which is for wings i.e. something with a span much higher than the chord and the thickness. $\endgroup$
    – sophit
    Jun 27, 2023 at 9:02
  • $\begingroup$ Thank you sophit. This paper is excellent $\endgroup$
    – Seth
    Jun 27, 2023 at 18:50
  • $\begingroup$ You're welcome 🖖 $\endgroup$
    – sophit
    Jun 27, 2023 at 19:12

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This 3D shape will not generate appreciable lift. It will not behave like an airfoil.

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