Item Details

Effects of Wall Cooling and Angle of Attack on Boundary-Layer Transition on Sharp Cones at M[mathematical Symbol for Infinity] = 7.4

by George G. Mateer
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], 1972.
Language
English
Series
NASA Technical Note
Summary
Tests were conducted on 5 deg and 15 deg half-angle sharp cones at wall-to-total-temperature ratios of 0.08 to 0.4, and angles of attack from 0 deg to 20 deg. The results indicate that (1) transition Reynolds numbers decrease with decreasing temperature ratio, (2) local transition Reynolds numbers decrease from the windward to the leeward side of the model, and (3) transition data on the windward ray of cones can be correlated in terms of the crossflow velocity gradient, momentum thickness Reynolds number, local Mach number, and cone half-angle.
Description
iv, 10 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Ames Research Center.
  • Cover title.
  • Bibliography: p. 7-8.
Series Statement
NASA technical note ; NASA TN D-6908
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| UIU c| UIU
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    a| UIUU
    100
    1
      
    a| Mateer, George G.
    245
    1
    0
    a| Effects of wall cooling and angle of attack on boundary-layer transition on sharp cones at M[mathematical symbol for infinity] = 7.4 c| by George G. Mateer.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1972.
    300
      
      
    a| iv, 10 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| NASA TN D-6908
    500
      
      
    a| Prepared at Ames Research Center.
    500
      
      
    a| Cover title.
    504
      
      
    a| Bibliography: p. 7-8.
    520
      
      
    a| Tests were conducted on 5 deg and 15 deg half-angle sharp cones at wall-to-total-temperature ratios of 0.08 to 0.4, and angles of attack from 0 deg to 20 deg. The results indicate that (1) transition Reynolds numbers decrease with decreasing temperature ratio, (2) local transition Reynolds numbers decrease from the windward to the leeward side of the model, and (3) transition data on the windward ray of cones can be correlated in terms of the crossflow velocity gradient, momentum thickness Reynolds number, local Mach number, and cone half-angle.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Laminar flow.
    650
      
    0
    a| Heat x| Transmission.
    650
      
    0
    a| Cone x| Aerodynamics.
    650
      
    0
    a| Boundary layer.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Ames Research Center.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106886184 y| 1972 r| pd q| bib

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