A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration with a wing of 45 degrees sweepback, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfo

Author:	Osborne, Robert S
Year:	1950
Document Type:	N/A
Series:	NACA Research Memorandums
Report Number:	NACA-RM-L50H08
Link:	https://digital.library.unt.edu/ark:/67531/metadc58530/