Hi I posted this a while back, Can i assume that no one has used the formula to determine stall speed? Not sure how to with the RAF48, no idea what the Coefficiant of Lift is, although the "new" airfoil probably has it someplace, or what to input with the density of air number. Anyone care to take a stab at it with the KR1 or 2?
> > https://www.quora.com/How-do-you-calculate-the-stall-speed-of-an-aircraft > > > Now from an engineering Point of View > The stall speed of an aircraft is dependent on four parameters, > > Air Density > Wing Area > Coefficient of Lift > Weight of the Aircraft > > > The exact formula is > V = ?( 2 W g / ? S Clmax ) > > Where, > V = Stall Speed > W = Weight of the aircraft > g = 9.81 (Acc. Due to Gravity) > ? = Density of Air > S = Wing Area > Clmax = Coefficient of Lift at Stall
