I have been trying to figure out (if even possible) how to calculate top speed of an aircraft if I know these:
MTOW weight = W = 220 kg
wing area S = 7.5 m^2
wing profile = Gottingen 533
GOE 533 AIRFOIL (goe533-il)
engine power = P = 20 Kw
propeller efficiency = H (eta) = 0.75
air density = p (rho) =1.056 kg/m^2
I pulled those values "from the hat"
If you are talented with this kind of stuff, could you show me step by step with those values how that kind of calculation should be done.