1950•Unpublished venueRequires access

Flight Measurements with the Douglas D-558-II (buaero No. 37974) Research Airplane : Determination of the Aerodynamic Center and Zero-lift Pitching-moment Coefficient of the Wing-fuselage Combination by Means of Tail-load Measurements in the Mach Num

John P Mayer, George M Valentine, Geraldine C Mayer

Abstract

Report presenting flight measurements of aerodynamic tail loads made on the Douglas D-558-II from which the variation with Mach number of the wing-fuselage aerodynamic center, static-longitudinal-stability parameter, the tail load per g, and the zero-lift wing-fuselage pitching-moment coefficient determined up to Mach number 0.87.

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Available abstract

Key concepts: Fuselage, Pitching moment, Airplane, Aerodynamics, Mach number, Wing, Lift coefficient, Wing loading