Coefficient of Lift, Does anyone know it? Options

[Matt Romanowski]

I've done tons of searching, but I haven't been able to find if anyone knows the coefficient of lift for a 914? I've found lots of Cd and Ca numbers, but I need the Cl for some data work.

Thanks!

[Dave_Darling]

It's not the frontal area, it's the planform area. More or less, the area of the shadow of the car when the sun is directly overhead.

One formula for lift is:

L = (1/2) d v2 s CL

* L = Lift, which must equal the airplane's weight in pounds
* d = density of the air. This will change due to altitude. These values can be found in a I.C.A.O. Standard Atmosphere Table.
* v = velocity of an aircraft expressed in feet per second
* s = the wing area of an aircraft in square feet
* CL = Coefficient of lift , which is determined by the type of airfoil and angle of attack.

Formula from: http://www.grc.nasa.gov/WWW/k-12/WindTunne...ft_formula.html

For our purposes, the L would be the 124.76N, d would be the density at sea level (29.92 inches of mercury), v would be whatever speed the 124.76N of lift was derived or measured at, and s would be the planform area mentioned above.

You'll have to do a mess of unit conversions to get all of the terms to agree, then plug the numbers in and solve for CL.

--DD