Aerodynamic characteristics of four wings of sweepback angles 0 degree, 35 degrees, 45 degrees, and 60 degrees, NACA 65A006 airfoil section, aspect ratio 4, and taper ratio 0.6 in combination with a fuselage at high subsonic Mach numbers and Mach num

Arvo A. Luoma
naca-rm-l51d13
Jun 1951

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.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51d13.pdf