Transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : analysis of pressure distribution of wing-fuselage configuration having a wing of 45 degrees sweptback, aspect ratio 4, t

Donald L. Loving, Bruce B. Estabrooks
naca-rm-l51f07
Sep 1951


A pressure-distribution investigation has been made in the Langley 8-foot high-speed tunnel of a wing-fuselage configuration as part of an NACA research program to determine effects of wing geometry on aerodynamic characteristics and to explore the nature of the flow over the configuration and the problem of interference between a wing and fuselage.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51f07.pdf