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
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE