Hence,
given shape of airfoil at a given angle of attack,
L = f(V∞, P, S, μloo, A∞)
(5.3)
and D and M are similar functions.
In principle, for a given airfoil at a given angle of attack, we could find the
variation of L by performing myriad wind tunnel experiments wherein V... Po
and a.. are individually varied and then
could twee to mala
out
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