Accession Number : AD0651903
Title : LONGITUDINAL AND DIRECTIONAL AERODYNAMIC CHARACTERISTICS OF SEVERAL HYPERSONIC AIRCRAFT CONFIGURATIONS.
Descriptive Note : Research and development rept.,
Corporate Author : DAVID TAYLOR MODEL BASIN WASHINGTON D C AERODYNAMICS LAB
Personal Author(s) : Krouse,John R. ; Ellis,Bertram K.
Report Date : JAN 1967
Pagination or Media Count : 28
Abstract : Wind tunnel tests were conducted at a Mach number of 9.45 to determine the aerodynamic characteristics of several conceptual hypersonic aircraft configurations consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, wing planform, and wing-tip deflection on static directional stability were determined. In addition, the effects of wing thickness on the aerodynamic efficiency were obtained. Decreasing body volume, extending the trailing edges, and deflecting the wing tips (toward or away from the fuselage) were all directionally stabilizing. Decreasing wing thickness significantly increased maximum untrimmed lift-to-drag ratios.
Descriptors : (*HYPERSONIC AIRCRAFT, *AERODYNAMICS), STABILITY, WINGS, THICKNESS, DIRECTION FINDING, WIND TUNNELS, FUSELAGES, AERODYNAMIC CONTROL SURFACES, DELTA WINGS, CYLINDRICAL BODIES, DEFLECTION
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE