Method for calculating theoretical pressure distribution over large class of flat wings at angle of attack, for Mach numbers greater than 1.0; formulas are worked out in detail for moderately and highly swept wings of arbitrary taper, and include formulas for integrated lift, pitching moment, and induced drag.
Theoretical lift of flat swept-back wings at supersonic speeds
Nat Advisory Committee Aeronautics -- Tech Note
1948
57 pages
20 Supp plates, Bibliography
Article (Journal)
English
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