An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback

M. Leroy Spearman
naca-rm-l9l08
Apr 1950


An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the longitudinal stability and control characteristics of a model of a supersonic airplane configuration at a Mach number of 1.40. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1950/naca-rm-l9l08.pdf