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Effect of modifications of aerodynamic characteristics of a single-stage-to-orbit vehicle at Mach 5.9Hypersonic stability, control, and performance characteristics were determined on a single-stage-to-orbit vehicle based on control-configured stability concepts. The configuration (0.006-scale model) had a large body with a small 50 deg swept wing. Two vertical-fin arrangements were investigated which consisted of a large center-line vertical tail and small wing-tip fins. The wing-tip fins had movable surfaces called controllers which could be deflected outward. Longitudinal and lateral directional characteristics were obtained over an angle-of-attack rage from 0 deg to 40 deg. The effects of tip-fin controller deflection on roll- and yaw-control characteristics at a sideslip angle of 0 deg were obtained. This investigation was conducted in the Langley 20 Inch Mach 6 Tunnel.
Document ID
19830008012
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bernot, P. T. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:84565
NASA-TM-84565
L-15504
Accession Number
83N16283
Funding Number(s)
PROJECT: RTOP 506-51-13-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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