By combined use of A. BUSEMANN second order approximation theory for pressure distribution over two-dimensional airfoil with straight leading edge and theory for loss in lift at tips of rectangular airfoil in supersonic flow, expressions for lift, drag, and moment coefficients and center of pressure are derived for rectangular type of wing. (See also - discussion n 6, 7, June p 335-6, July p 409-10, 432)
Aerodynamic characteristics of rectangular wings at supersonic speeds
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 14 , n 2
1947
7 pages
Article (Journal)
English
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Aerodynamic performance of Delta wings at supersonic speeds
Engineering Index Backfile | 1948
|Aerodynamic performance of Delta wings at supersonic speeds
Engineering Index Backfile | 1948
|Aerodynamic performance of Delta wings at supersonic speeds
Engineering Index Backfile | 1947
|