I went you these links and understand a bit better but I dont have the Clmax curve for the RAF48 or the "new" wing (at least the latter must be around someplace). BTW I have never heard of this being discussed to consider an aircraft for LSA compliant, has anyone else? Anyway not sure what to use for air density. But its four numbers into the formula and two are easy (aircraft weight and wing area). I would like to practice this with a KR1 or KR2 built to plans then I can adjust things like gross weight and wing area to bring it within the envelope if necessary.
What is Clmax and how to put a number to air density at sea level standard day? (I am NOT that good at math) 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
