The effects on the aerodynamic characteristics of reversing the wing of a triangular wing-body combination at transonic speeds as determined by the NACA wing-flow method

James M. McKay, Albert W. Hall
naca-rm-l51h23
Oct 1951


Tests were made by the NACA wing-flow method at Mach numbers from 0.75 to 1.075 to determine the effect on the aerodynamic characteristics of reversing a triangular wing with a 6-percent-thick biconvex section.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51h23.pdf