Arvo A. Luoma
An investigation was made in the Langley 8-foot high-speed tunnel of the effect of sweepback angle on wing-fuselage characteristics at subsonic Mach numbers up to approximately 0.95 and at one supersonic Mach number of 1.2. Sweepback angles of 0, 35, 45, and 60 degrees based on the 25-percent-chord line were investigated. Lift, drag, and pitching-moment coefficients were determined from strain-gage measurements.
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