Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method

Albert W. Hall, James M. McKay
naca-rm-l51f01
Aug 1951


Tests were made by the NACA wing-flow method at Mach numbers from 0.75 to 1.075 to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Two models had wings of aspect ratio 2.31 (half-apex angle of 30 degrees), one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section; the other two models had wings of aspect ratio 4.00 (half-apex angle of 45 degrees), one with an NACA 65-006 airfoil section and one with a 6-percent-thick double-wedge section.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51f01.pdf