1955•Unpublished venueRequires access

Static longitudinal and lateral stability and control characteristics of a model of a 35 degree swept-wing airplane at a Mach number of 1.41

Edward B Palazzo, M Leroy Spearman

Abstract

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a model of a 35 degree swept-wing airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on aerodynamic characteristics were also investigated.

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Available abstract

Key concepts: Fuselage, Airplane, Wing, Longitudinal static stability, Aerodynamics, Mach number, Supersonic speed, Camber (aerodynamics)