CL help
I am trying to find the Coefficient of Lift for a Dash 8 Q400 for my A/C engineering studies at Uni. I am pretty new to the world of aircraft engineering so need some clarification in what I am doing exactly. If Cl = W/(1/2PV^2S) and I have a mid cruise weight, cruise altitude and cruise velocity should I sub into the V a value of true or indicated airspeed in m/s? How do I find my true airspeed at altitude?
Any help is much appreciated,
Cheers