Load distribution over a fuselage in combination with a swept wing at small angles of attack and transonic speeds

Maurice D. White, Bonne C. Look
naca-rm-a51h15
Nov 1951


Free-fall tests were made of a wing-body configuration having a 45 degree swept-back cambered and twisted wing of aspect ratio 6 on a fuselage of fineness ratio 12.4. The test Mach numbers ranged from 0.85 to 1.06 and the Reynolds numbers from 2,750,000 to 5,600,000.

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http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-a51h15.pdf