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IN the paper by Plotkin,1 first-order corrections to slender wing theory2 were developed due to spanwise thickness and camber distributions. The velocity potential <f>(x, y, z) calculated in the paper1 actually corresponds to the flow having zero normal velocity at the body contour and a vertical velocity at infinity proportional to the angle of attack [<f>z(x, y, \z\ -> oo) = Ua

Comment on "Thickness and Camber Effects in Slender Wing Theory"