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An overview of selected NASP aeroelastic studies at the NASA Langley Research CenterFollowing an initial discussion of the NASP flight environment, the results of recent aeroelastic testing of NASP-type highly swept delta-wing models in Langley's Transonic Dynamics Tunnel (TDT) are summarized. Subsonic and transonic flutter characteristics of a variety of these models are described, and several analytical codes used to predict flutter of these models are evaluated. These codes generally provide good, but conservative predictions of subsonic and transonic flutter. Also, test results are presented on a nonlinear transonic phenomena known as aileron buzz which occurred in the wind tunnel on highly swept delta wings with full-span ailerons. An analytical procedure which assesses the effects of hypersonic heating on aeroelastic instabilities (aerothermoelasticity) is also described. This procedure accurately predicted flutter of a heated aluminum wing on which experimental data exists. Results are presented on the application of this method to calculate the flutter characteristics of a fine-element model of a generic NASP configuration. Finally, it is demonstrated analytically that active controls can be employed to improve the aeroelastic stability and ride quality of a generic NASP vehicle flying at hypersonic speeds.
Document ID
19910029821
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Spain, Charles V.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Soistmann, David L.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Parker, Ellen C.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Gibbons, Michael D.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Gilbert, Michael G.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
October 1, 1990
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 90-5218
Accession Number
91A14444
Distribution Limits
Public
Copyright
Other

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