Analytical and experimental investigation of inlet-engine matching for turbojet-powered aircraft at Mach numbers up to 2.0

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

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Description

An analysis of inlet-turbojet-engine matching for a range of Mach numbers up to 2.0 indicates large performance penalties when fixed-geometry inlets are used. Use of variable-geometry inlets, however, nearly eliminates th The analysis was confirmed experimentally by investigating at Mach numbers of 0, 0.63, and 1.5 to 2.0 two single oblique-shock-type inlets of different compression-ramp angles, which simulated a variable-geometry configuration. The experimental investigation indicated that total-pressure recoveries comparable withose attainable with well designed nose inlets were obtained with the side inlets when all the boundary layer ahead of the inlets was removed. Serious drag penalties resulted at a Mach ... continued below

Physical Description

31 p. : ill.

Creation Information

Schueller, Carl F. & Esenwein, Fred T. February 13, 1952.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 71 times . More information about this report can be viewed below.

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  • Main Title: Analytical and experimental investigation of inlet-engine matching for turbojet-powered aircraft at Mach numbers up to 2.0
  • Series Title: NACA Research Memorandums

Description

An analysis of inlet-turbojet-engine matching for a range of Mach numbers up to 2.0 indicates large performance penalties when fixed-geometry inlets are used. Use of variable-geometry inlets, however, nearly eliminates th The analysis was confirmed experimentally by investigating at Mach numbers of 0, 0.63, and 1.5 to 2.0 two single oblique-shock-type inlets of different compression-ramp angles, which simulated a variable-geometry configuration. The experimental investigation indicated that total-pressure recoveries comparable withose attainable with well designed nose inlets were obtained with the side inlets when all the boundary layer ahead of the inlets was removed. Serious drag penalties resulted at a Mach number of 2.0 from the use of blunt-cowl leading edges. However, sharp-lip inlets produced large losses in thrust for the take-off condition. These thrust penalties which are associated with the the low-speed operation of the sharp-lip inlet designs can probably be avoided without impairing the supersonic performance of the inlet by the use of auxiliary inlets or blow-in doors.

Physical Description

31 p. : ill.

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  • Accession or Local Control No: 93R17183
  • URL: http://hdl.handle.net/2060/19930087893 External Link
  • Report No.: NACA-RM-E51K20
  • Center for AeroSpace Information Number: 19930087893
  • Archival Resource Key: ark:/67531/metadc59862

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • February 13, 1952

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

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  • April 12, 2018, 6:45 p.m.

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Schueller, Carl F. & Esenwein, Fred T. Analytical and experimental investigation of inlet-engine matching for turbojet-powered aircraft at Mach numbers up to 2.0, report, February 13, 1952; (digital.library.unt.edu/ark:/67531/metadc59862/: accessed October 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.