Shock drag of sweptback wing originates mainly from roots, where "S" shaped wing streamlines are constrained to move along side of fuselage; accurate method of calculating free stream shape of these streamlines, used to design model of fairing for EC.1240 wing sweptback 65° from flat plate.
Tests of fairing to reduce drag of supersonic swept-wing root
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 22 , n 3
1955
Article (Journal)
English
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