Wave drag equations derived for rhombic-profile tapered wings with maximum thickness line swept less than Mach lines; variations in drag with taper ratio, aspect ratio, sweepback, and Mach number determined; calculations presented for representative plan forms and for family of wings having equal root bending stress.
Supersonic wave drag of nonlifting sweptback tapered wings with Mach lines behind line of maximum thickness
Nat Advisory Committee Aeronautics -- Tech Note
1948
34 pages
Report
English
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Engineering Index Backfile | 1947
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