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Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplaneThe static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was six at a Reynolds number, based on model fuselage length, of about 13,700,000. The test angle-of-attack range was 4 to 20 D at constant angles of sideslip of 0, 2, and 4 deg. The elevons were deflected from 10 to -15 D for pitch control. Roll and yaw control were investigated. Experimental aerodynamic characteristics are compared with analytical elements.
Document ID
19780022112
Document Type
Technical Publication (TP)
Authors
Dillon, J. L.
(NASA Langley Research Center Hampton, VA, United States)
Pittman, J. L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1249
L-12183
Funding Number(s)
PROJECT: RTOP 505-11-33-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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