An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback : a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Norman F. Smith, Julian H. Kainer, Robert A. Webster
naca-rm-l51c06
Apr 1951


A pressure-distribution investigation of the wing, in the presence of the fuselage, of a supersonic aircraft configuration has been conducted in the Langley 4- by 4-foot supersonic tunnel at a Mach number of 1.40 and a Reynolds number, based on the mean aerodynamic chord, of 0.598 X 10 (superscript 6).

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51c06.pdf