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.
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?
Please advise. Thank you
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