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Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in AirA 0.0196-scale model of the HL-20 lifting-body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 2 deg to 41 deg, the sideslip angles were 0 deg, 2 deg, and -2 deg, and the test Reynolds number was 1.06 x 10 E6 based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 deg. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.
Document ID
19990117251
Document Type
Technical Memorandum (TM)
Authors
Scallion, William I. (NASA Langley Research Center Hampton,VA United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-1999-209357
L-17867
NAS 1.15:209357
Funding Number(s)
PROJECT: RTOP 242-80-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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