Item Details

Aerodynamic Effects of Some Configuration Variables on the Aeroelastic Characteristics of Lifting Surfaces at Mach Numbers From 0.7 to 6.86

by Perry W. Hanson
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
Results of flutter tests on some simple all-movable-control-type models are given. One set on models, which had a square planform with double-wedge airfoils with four different values of leading- and trailing-edge radii from 0 to 6 percent chord and airfoil thickness of 9, 11, 14, and 20 percent chord, was tested at Mach numbers from 0.7 to 6.86. The bending-to-torsion frequency ratio was about 0.33. The other set of models, which had a tapered planform with single-wedge and double-wedge airfoils with thickness of 3, 6, 9, and 12 percent chord, was tested at Mach numbers from 0.7 to 3.98 and a frequency ratio of about 0.42.
Description
51 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19980230676.
  • "NASA TN D-984."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "November 1961."
  • Cover title.
  • Includes bibliographical references (p. 16).
Series Statement
NASA technical note ; D-984
Other Forms
Also available from the NASA Technical Reports Server.
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Aerodynamic effects of some configuration variables on the aeroelastic characteristics of lifting surfaces at Mach numbers from 0.7 to 6.86 / c| by Perry W. Hanson.
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    a| 51 p. : b| ill. ; c| 26 cm.
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    a| Document ID: 19980230676.
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    a| "Langley Research Center, Langley Air Force Base, Va."
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    a| "November 1961."
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    a| Cover title.
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    a| Includes bibliographical references (p. 16).
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    a| Results of flutter tests on some simple all-movable-control-type models are given. One set on models, which had a square planform with double-wedge airfoils with four different values of leading- and trailing-edge radii from 0 to 6 percent chord and airfoil thickness of 9, 11, 14, and 20 percent chord, was tested at Mach numbers from 0.7 to 6.86. The bending-to-torsion frequency ratio was about 0.33. The other set of models, which had a tapered planform with single-wedge and double-wedge airfoils with thickness of 3, 6, 9, and 12 percent chord, was tested at Mach numbers from 0.7 to 3.98 and a frequency ratio of about 0.42.
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    a| Also available from the NASA Technical Reports Server.
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    a| Mode of access: Internet.
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    a| Lift (Aerodynamics)
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    a| Aeroelasticity.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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