Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 4 - Performance of Modified Compressor, Part 4, Performance of Modified Compressor

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Description

The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet velocity, in a revised X24C-4B turbojet engine is presented and compared with the performance of the compressor in the original engine. Performance data were obtained from an investigation of the revised engine in the MACA Cleveland altitude wind tunnel. Compressor performance data were obtained for engine operation with four exhaust nozzles of different outlet area at simulated altitudes from 15,OOO to 45,000 feet, simulated flight Mach numbers from 0.24 to 1.07, and engine speeds from 4000 to 12,500 rpm. The data cover a range of corrected engine speeds ... continued below

Physical Description

37 p. : ill.

Creation Information

Thorman, H. Carl & Dupree, David T. December 22, 1947.

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

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  • Main Title: Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 4 - Performance of Modified Compressor, Part 4, Performance of Modified Compressor
  • Series Title: NACA Research Memorandums

Description

The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet velocity, in a revised X24C-4B turbojet engine is presented and compared with the performance of the compressor in the original engine. Performance data were obtained from an investigation of the revised engine in the MACA Cleveland altitude wind tunnel. Compressor performance data were obtained for engine operation with four exhaust nozzles of different outlet area at simulated altitudes from 15,OOO to 45,000 feet, simulated flight Mach numbers from 0.24 to 1.07, and engine speeds from 4000 to 12,500 rpm. The data cover a range of corrected engine speeds from 4100 to 13,500 rpm, which correspond to compressor Mach numbers from 0.30 to 1.00.

Physical Description

37 p. : ill.

Notes

"IV."

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  • URL: http://hdl.handle.net/2060/20050019244 External Link
  • Report No.: NACA-RM-SE7L22A-Pt-4
  • Center for AeroSpace Information Number: 20050019244
  • Archival Resource Key: ark:/67531/metadc64086

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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

  • December 22, 1947

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • April 24, 2018, 11:07 a.m.

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Thorman, H. Carl & Dupree, David T. Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 4 - Performance of Modified Compressor, Part 4, Performance of Modified Compressor, report, December 22, 1947; (digital.library.unt.edu/ark:/67531/metadc64086/: accessed December 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.