![]() The problem that it sounds to good to be true.Ģ) I found online a simpler equation (cl = clmax(AR/(AR+2)). This means that the Airfoil Data Clmax is still relevant but their is a increased amount of drag necessary to achieve it. The formula it gives for this change includes aspect ratio, taper and sweep. Here are the 2 concepts confusing me:ġ) My McCormick aerodynamics text shows that for a finite wing the Cl max value doesn't change so much as the angle of attack at which its reached changes, along with the whole cl vs angle of attach curve slope. I have done some research and found myself conflicted and confused. I know the factors that effect CL in a finite wing (Aspect Ratio, Sweep, and Taper ratio). I am trying to calculate wing size and the max Cl value is obviously important.
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