NDLI: Aerodynamic characteristics at mach 6 of a wing-body concept for a hypersonic research airplane

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Aerodynamic characteristics at mach 6 of a wing-body concept for a hypersonic research airplane

Content Provider	NASA Technical Reports Server (NTRS)
Author	Dillon, J. L. Pittman, J. L.
Copyright Year	1978
Description	The 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.
File Size	12055716
Page Count	60
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19780022112
Archival Resource Key	ark:/13960/t5jb0zh59
Language	English
Publisher Date	1978-08-01
Access Restriction	Open
Subject Keyword	Aerodynamics Directional Stability Body-wing and Tail Configurations Lateral Stability Hypersonic Wind Tunnels Wind Tunnel Models Aerodynamic Characteristics Hypersonic Aircraft Longitudinal Stability Aircraft Control Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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