Item Details

Investigation of Flow Fields Within Large-Scale Hypersonic Inlet Models

by A. Vernon Gnos ... [et al.]
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], 1973.
Language
English
Series
NASA Technical Note
Summary
Analytical and experimental investigations were conducted to determine the internal flow characteristics in model passages representative of hypersonic inlets for use at Mach numbers to about 12. The passages were large enough to permit measurements to be made in both the core flow and boundary layers. The analytical techniques for designing the internal contours and predicting the internal flow-field development accounted for coupling between the boundary layers and inviscid flow fields by means of a displacement-thickness correction. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide high internal performance with an approximately uniform static-pressure distribution at the throat station. The models were tested in the Ames 3.5-Foot Hypersonic Wind Tunnel at a nominal free-stream Mach number of 7.4 and a unit free-stream Reynolds number of 8.86 X one million per meter.
Description
vi, 169 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Research prepared at Ames Research Center and Fairchild Industries.
  • Cover title.
  • Bibliography: p. 38-39.
Series Statement
NASA technical note ; NASA TN D-7150
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Investigation of flow fields within large-scale hypersonic inlet models c| by A. Vernon Gnos ... [et al.].
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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| 1973.
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    a| vi, 169 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| NASA TN D-7150
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    a| Research prepared at Ames Research Center and Fairchild Industries.
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    a| Cover title.
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    a| Bibliography: p. 38-39.
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    a| Analytical and experimental investigations were conducted to determine the internal flow characteristics in model passages representative of hypersonic inlets for use at Mach numbers to about 12. The passages were large enough to permit measurements to be made in both the core flow and boundary layers. The analytical techniques for designing the internal contours and predicting the internal flow-field development accounted for coupling between the boundary layers and inviscid flow fields by means of a displacement-thickness correction. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide high internal performance with an approximately uniform static-pressure distribution at the throat station. The models were tested in the Ames 3.5-Foot Hypersonic Wind Tunnel at a nominal free-stream Mach number of 7.4 and a unit free-stream Reynolds number of 8.86 X one million per meter.
    538
      
      
    a| Mode of access: Internet.
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    a| Aerodynamics, Hypersonic.
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    a| Jet engines x| Air intakes.
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    a| DeCarlo, Joseph P.
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    a| Sanator, Robert J.
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    a| Seebaugh, William R.
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    a| Watson, Earl C.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Fairchild Industries. b| Fairchild Republic Division.
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    a| Ames Research Center.
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