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Question

I am trying to compute aerodynamic coefficients from experimental data. CL = L [kgf] x 9.81

L [N] -0.240 x 9.81

____________ = ____________ = ______________

q [Pa] x S [m^2] q [Pa] x S [m^2] q [Pa] x S [m^2]

This is co efficient of lift. Data is from a wind tunnel.

Wing/Airfoil characteristics:

b=12 inch/m c= 4 (inch/m) S= 48 (inch^2/m^2) C (with line above)= 4 AR=b^2 / S = 3 TR=1 deg=0

Static air data

P=29.32 (inch HG) Tem (T) = 74.4 [Pa] - is this 31397.331? T (0 degrees C/K) = 27.6 degrees celcius/296.71 k P [kg/m^3]=1.1658 (is this air density?)

So how do I find q? [Pa] - (above?) S (do I take 48 square it and divide by m^2-but what is m?) finally, times by m^2 again...what is m?

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