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Longitudinal Stability and Drag Characteristics at Mach Numbers from 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained from Rocket-propelled Models

John C Mcfall, Antonio Vitale, John Morrow

Abstract

Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.

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Available abstract

Key concepts: Airplane, Drag divergence Mach number, Drag, Fuselage, Lift-induced drag, Zero-lift drag coefficient, Mach number, Drag coefficient