Two cases investigated are given length and thickness and given length and enclosed area; indirect methods of calculus of variations are employed, and it is shown that optimum airfoil is diamond shape for case 1 and is biconvex for case 2; if linear theory is employed, maximum lift-to-drag ratio airfoil has maximum thickness at midchord and is symmetric with respect to chord; if nonlinear theory is used, maximum lift-to-drag ratio airfoil has maximum thickness in rear half and is asymmetric with respect to chord (upper contour is thicker than lower contour). (28744)
Maximum lift-to-drag ratio airfoils at moderate supersonic speeds
AIAA J
AIAA Journal ; 7 , n 3
1969
7 pages
Article (Journal)
English
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