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Equation for stall speed, wing loading, speed?
Thanks. I'm reading an article
http://www.masportaviator.com/ah.asp...&ID=72&index=1 discussing prop selection, and he mentions an equation for calculating stall speed as a function of speed and wing loading, then he does not include the equation. Does anybody know of such/ Thanks Jim 




The 'full' formula (in S.I. units) is:
V = sq root (W x 9.81/(1/2p x S x Cl_max)) where: V = Stall speed M/s p (rho) = air density KG/M^3 S = wing area M^2 Cl_max = Coefficient of lift at stall W = weight KG The simplified 'rule of thumb' version posted above assumes that you are flying at sea level and uses an assumed Cl max. Steve 


Christchurch, New Zealand
Joined Jun 2006
6,794 Posts

Or more readably if your computer does all these characters:
V = √( 2 W g / ρ S Clmax ) g = 9.81 m s^2 ρ is rho The rest as above. 



Quote:
Thanks Steve and Andrew. Not sure how I'd get air density or coefficient of lift at stall? Thanks a lot. Jim 



Joined Jun 2005
236 Posts

air density is about 1.2 kg/m^3 at sea level, max airfoil Cl must be determined from airfoil polar graphs ( Cl/AOA or Cl/Cd, typically).




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Cl max varies according to airfoil used, wing aspect ratio and the size and speed of the model... Somewhere in the range 1 to 1.5 would be reasonable, small slow flying models being closer to 1 and larger and faster models closer to 1.5 Steve 




Is it Possible that The stall Speed Is Lower than the speed i used for Carculate the Lift?? The wight in the stall speed formula i used the total Lift from the lift Carculation.. but even the stall speed is about 1/5 Lower than i think it shuld be



Christchurch, New Zealand
Joined Jun 2006
6,794 Posts

I don't understand the question… the equation above is for stall speed in terms of the actual weight of the aircraft, you don't need to calculate any lift forces because they are already rolled into the formula above.




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I Thougt, If I take the Lift Created From the wing(Carculated by formula) Insteed of the actual weight of the aircraft, In that way i can check if the formula is right. For example if i Carculate Lift For 100 Km/h and use the same Data in the stall speed carculation, i would come up with the same Speed (100km/h) but insteed I came up with a stall speed of 72 Km/h. i just wondred if the stall speed use to be lie lower than the speed I carculated lift with? Im about to do a Design Templet, For making the design better and also adjust it after the requerments i want. Thanx // Luft 46' Design 




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some additions:
you have to separate cl and cl_max. for stall speed you have to use cl_max, for all other flight conditions you have to use cl. cl depends from alpha (AOA) and has a maximum with cl_max > cl < cl_max for stallspeed the lift is the weight of the model. for climbing lift > wheigt!. if you are flying faster than stallspeed and NOT climbing (> cruise), then cl < cl_max and alpha < alpha_max. 



Quote:
If the lift was greater than the weight the aircraft would be accelerating upward, i.e. the rate of ascent would be constantly increasing. It's 'excess' thrust that makes an aircraft climb, not 'excess' lift. Stall speed itself is a somewhat missleading term because it's only applicable if the aircraft is flying straight and level. If the aircraft is turning then stall speed will increase, in fact try to turn too hard and it's quite possible to stall when flying at flat out speed (or pull the wings off, whichever comes first . Steve 

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