Item Details

Theoretical and Experimental Longitudinal Aerodynamic Characteristics of an Aspect Ratio 0.25 Sharp-Edge Delta Wing at Subsonic, Supersonic, and Hypersonic Speeds

by Charles H. Fox, Jr., and John E. Lamar
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], 1974.
Language
English
Series
NASA Technical Note
Abstract
The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
Description
43 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Langley Research Center.
  • Cover title.
  • Includes bibliographical references (p. 14-15).
Series Statement
NASA technical note ; NASA TN D-7651
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Theoretical and experimental longitudinal aerodynamic characteristics of an aspect ratio 0.25 sharp-edge delta wing at subsonic, supersonic, and hypersonic speeds / c| by Charles H. Fox, Jr., and John E. Lamar.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1974.
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    a| 43 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| NASA TN D-7651
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    a| Prepared at Langley Research Center.
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    a| Cover title.
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    a| Includes bibliographical references (p. 14-15).
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    3
      
    a| The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
    538
      
      
    a| Mode of access: Internet.
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    a| Lift (Aerodynamics)
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    a| Vortex-motion.
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    a| Leading edges (Aerodynamics)
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    a| Airplanes x| Wings, Triangular.
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    a| Lamar, John E.
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    a| Langley Research Center.
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