Contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan model of a supersonic airplane configuration at transonic speeds from tests by the NACA wing-flow method

Norman S. Silsby, James M. McKay
naca-rm-l51e01
Jul 1951


An investigation has been made by the NACA wing-flow method at transonic speeds to determine the contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan airplane model having a long slender fuselage and a straight wing and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections 4.6 percent of the chord in thickness.

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http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51e01.pdf