Item Details

Calculation of Unsteady Transonic Aerodynamics for Oscillating Wings With Thickness

by S.Y. Ruo and J.G. Theisen
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1975.
Language
English
Series
NASA Contractor Report
Summary
An analytical approach is presented to account for some of the nonlinear characteristics of the transonic flow equation for finite thickness wings undergoing harmonic oscillation at sonic flight speed in an inviscid, shock-free fluid. The thickness effect is accounted for in the analysis through use of the steady local Mach number distribution over the wing at its mean position by employing the local linearization concept and a coordinate transformation. Computed results are compared with that of the linearized theory and experiments. Based on the local linearization concept, an alternate formulation avoiding the limitations of the coordinate transformation method is presented.
Description
iv, 51 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2259."
  • Performing organization report no.: LG74ER0129.
  • "August 1975."
  • Cover title.
  • Includes bibliographical references (p. 37-40).
Series Statement
NASA contractor report ; NASA CR-2259
Other Forms
Also available via Internet from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 6/23/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750019958%5f1975019958.pdf.
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Ruo, S. Y.
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    a| Calculation of unsteady transonic aerodynamics for oscillating wings with thickness / c| by S.Y. Ruo and J.G. Theisen.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1975.
    300
      
      
    a| iv, 51 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2259
    500
      
      
    a| "NASA CR-2259."
    500
      
      
    a| Performing organization report no.: LG74ER0129.
    500
      
      
    a| "August 1975."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 37-40).
    520
      
      
    a| An analytical approach is presented to account for some of the nonlinear characteristics of the transonic flow equation for finite thickness wings undergoing harmonic oscillation at sonic flight speed in an inviscid, shock-free fluid. The thickness effect is accounted for in the analysis through use of the steady local Mach number distribution over the wing at its mean position by employing the local linearization concept and a coordinate transformation. Computed results are compared with that of the linearized theory and experiments. Based on the local linearization concept, an alternate formulation avoiding the limitations of the coordinate transformation method is presented.
    530
      
      
    a| Also available via Internet from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 6/23/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750019958%5f1975019958.pdf.
    536
      
      
    a| Prepared by Lockheed-Georgia Company, Marietta, Ga. for Langley Research Center b| NAS1-11156
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Aeroelasticity.
    650
      
    0
    a| Aerodynamics, Transonic x| Computer simulation.
    650
      
    0
    a| Oscillating wings (Aerodynamics) x| Computer simulation.
    650
      
    7
    a| Stability derivatives. 2| nasat
    650
      
    7
    a| Oscillations. 2| nasat
    650
      
    7
    a| Linearization. 2| nasat
    650
      
    7
    a| Wing oscillations. 2| nasat
    650
      
    7
    a| Unsteady flow. 2| nasat
    650
      
    7
    a| Unsteady aerodynamics. 2| nasat
    650
      
    7
    a| Transonic flow. 2| nasat
    650
      
    7
    a| Thickness ratio. 2| nasat
    700
    1
      
    a| Theisen, J. G.
    710
    2
      
    a| Langley Research Center.
    710
    2
      
    a| Lockheed-Georgia Company.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106908970 y| 1975 r| pd q| bib

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