Accession Number : AD0634562

Title :   LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL HYPERSONIC AIRCRAFT CONFIGURATIONS AT A MACH NUMBER OF 6.26

Descriptive Note : Research and development rept.

Corporate Author : DAVID TAYLOR MODEL BASIN WASHINGTON DC AERODYNAMICS LAB

Personal Author(s) : Krouse, John R ; Ellis, Bertram K

PDF Url : AD0634562

Report Date : May 1966

Pagination or Media Count : 43

Abstract : Wind-tunnel tests were conducted at a Mach number of 6.26 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to- drag ratios of all high-wing configurations varied slightly over an angle-of- attack range of 0 degrees to 12 degrees reaching maximum values of roughly 3.2 near 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.6 near 10 degrees. In all cases, fuselage base drag accounted for less than 10 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were stable but unbalanced; whereas several high-wing configurations were both stable and balanced.

Descriptors :   *HYPERSONIC AIRCRAFT, *HYPERSONIC CHARACTERISTICS, *WING BODY CONFIGURATIONS, AERODYNAMIC CHARACTERISTICS, ANGLE OF ATTACK, CONICAL BODIES, CYLINDRICAL BODIES, DELTA WINGS, DRAG, FUSELAGES, LIFT, MODEL TESTS, WIND TUNNEL MODELS

Subject Categories : Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE