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?