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Aerothermoelastic Analysis of a NASP-Like Vertical FinSeveral aeroelastic stability analyses for a vertical fin similar to that of the National Aero-Space Plane are described. The objectives of the study were to design and obtain an experimental data base for a supersonic wind-tunnel model of the fin in order to examine the effects of thermal loading on the flutter characteristics. This paper describes the preliminary efforts to design the wind-tunnel model, including several of the geometric parameter variations that were analyzed. The dominant flutter mechanism involved a flap vibration mode and a fin bending mode. Variation of the thicknesses of flap and root flexures, used to attach the flap to the fin, and the fin to a support, significantly affected the flutter boundary. Uniform thermal loads, affecting only material properties, had little effect, as did the application of different uniform temperatures to each side of the fin. In contrast, the application of significant chord-wise thermal gradients induced stresses which reduced the flutter dynamic pressure by as much as 37 percent. For less extreme distributed loading, the low-aspect ratio fin was relatively unaffected.
Document ID
20080032814
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Rodgers, John P.
(Duke Univ. Durham, NC, United States)
Date Acquired
August 24, 2013
Publication Date
April 13, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA Paper-92-2400
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC 33rd Structures, Structural Dynamics, and Materials Conference
Location: Dallas, TX
Start Date: April 13, 1992
End Date: April 15, 1992
Sponsors: American Society of Civil Engineers, American Society for Composites, American Society of Mechanical Engineers, American Helicopter Society, Inc., American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NASP GWP#71
Distribution Limits
Public
Copyright
Other

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