In this video you will learn about Chordwise Distribution and how to calculate how to make the load on the wing.
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Chordwise Distribution, how we distribute the air load along the chord. These two gentlemen, Birnbaum and Glauert, came up with some calculations back in the early 1900s. We start with an airfoil with a small deflected trailing edge device. They theorized there's three different forces acting on this airfoil: one that's derived from flatplate one from camber, and one from deflection. The flatplate distribution looks something like this, it has nonzero lift but zero pitching moment. The camber has no lift but a nonzero moment the same with deflation. By combining all these three together you and up with the final distribution looks like that. So if this section of wing is producing 5 pounds of lift we could split it up accordingly and we know how to make the load on the wing.
