Large-scale flight measurements of zero-lift drag at Mach numbers from 0.8 to 1.6 of a wing-body combination having an unswept 4.5 percent thick wing with modified hexagonal sections

Eugene D. Schult
naca-rm-l51a15
Mar 1951


An investigation of zero-lift drag of a fin-stabilized wing-body combination was made from high-subsonic to supersonic speeds in the Reynolds number range from 8 X 10(superscript 6) to 24 X 10(superscript 6). The wing was unswept about the 74.5-percent-chord line, had an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections.

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