I am attempting to use XFoil to generate a list of coefficients of a given airfoil at a range of speeds.

The first issue I faced is that it appears with XFoil, you give it a Reynolds number (which varies by speed) and an Angle of attack, and it outputs the Coefficients of Lift and drag etc.

What I need, however, is to input a range of subsonic mach numbers (or various reynolds numbers) and for it to output the:

  • Lift Coefficient
  • Drag Coefficient
  • Max AOA (Departure)
  • Maximum possible Lift Coefficient

How would I go about this using XFoil or any other similar program?

  • $\begingroup$ might also try CFD online $\endgroup$
    – Phil Sweet
    Dec 5 '20 at 0:20
  • $\begingroup$ Will do, thanks. $\endgroup$
    – S.Stevens
    Dec 5 '20 at 22:10

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