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Investigation of Low-Subsonic Flight Characteristics of a Model of a Flat-Bottom Hypersonic Boost-Glide Configuration Having a 78 deg Delta WingAn investigation of the low-subsonic stability and control characteristics of a model of a flat-bottom hypersonic boost-glide configuration having 78 deg sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg angle of attack and unstable at angles of attack of about 25 deg and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg angle of attack.
Document ID
19980237090
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Paulson, John W. (NASA Langley Research Center Hampton, VA United States)
Shanks, Robert E. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1959
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-X-201
L-452
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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