Investigation of effects of inlet-air velocity distortion on performance of turbojet engine

One of 5,165 reports in the series: NACA Research Memorandums available on this site.

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Description

To determine effect of nonuniform inlet-air velocities, a full scale, axial-flow turbojet engine was investigated in Lewis altitude wind tunnel at altitudes from 20,000 to 50,000 feet, 0.21 flight Mach number and corrected engine speeds from 77.3 percent of rated speed to rated speed. Total-pressure variations as large as 103 pounds per square foot in radial direction and 90 pounds per square foot in circumferential direction at 30,000 feet were obtained. With the distortions investigated, net thrust varied between 0.95 and 1.03 of the thrust with uniform inlet-air distribution. Similarly the ratio of specific fuel consumption varied from 1.00 to ... continued below

Physical Description

41 p. : ill.

Creation Information

Conrad, E. William & Sobolewski, Adam E. September 13, 1950.

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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 89 times . More information about this report can be viewed below.

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  • Main Title: Investigation of effects of inlet-air velocity distortion on performance of turbojet engine
  • Series Title: NACA Research Memorandums

Description

To determine effect of nonuniform inlet-air velocities, a full scale, axial-flow turbojet engine was investigated in Lewis altitude wind tunnel at altitudes from 20,000 to 50,000 feet, 0.21 flight Mach number and corrected engine speeds from 77.3 percent of rated speed to rated speed. Total-pressure variations as large as 103 pounds per square foot in radial direction and 90 pounds per square foot in circumferential direction at 30,000 feet were obtained. With the distortions investigated, net thrust varied between 0.95 and 1.03 of the thrust with uniform inlet-air distribution. Similarly the ratio of specific fuel consumption varied from 1.00 to 1.04. Within the arrange of this investigation the effects of nonuniform inlet velocity were not serious for the engine investigated.

Physical Description

41 p. : ill.

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  • Accession or Local Control No: 93R15672
  • URL: http://hdl.handle.net/2060/19930086382 External Link
  • Report No.: NACA-RM-E50G11
  • Center for AeroSpace Information Number: 19930086382
  • Archival Resource Key: ark:/67531/metadc58625

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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

  • September 13, 1950

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

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  • June 6, 2018, 11:40 a.m.

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Conrad, E. William & Sobolewski, Adam E. Investigation of effects of inlet-air velocity distortion on performance of turbojet engine, report, September 13, 1950; (digital.library.unt.edu/ark:/67531/metadc58625/: accessed December 9, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.