Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, 3: Over-All Performance of Compressor

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Description

An investigation was conducted to determine the performance characteristics of the rotor and inlet guide vanes used in the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. Outlet stators used in the engine were omitted to facilitate study of the supersonic rotor. The extent of the deviation from design performance indicates that the design-shock configuration was not obtained. A maximum pressure ratio of 2.26 was obtained at an equivalent tip speed of 1614 feet per second and an adiabatic efficiency of 0.61. The maximum efficiency obtained was 0.79 at an equivalent tip speed of 801 feet per second and a ... continued below

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16 p. : ill.

Creation Information

Hartmann, Melvin J. & Tysl, Edward R. 1949.

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

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  • Main Title: Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, 3: Over-All Performance of Compressor
  • Series Title: NACA Research Memorandums

Description

An investigation was conducted to determine the performance characteristics of the rotor and inlet guide vanes used in the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. Outlet stators used in the engine were omitted to facilitate study of the supersonic rotor. The extent of the deviation from design performance indicates that the design-shock configuration was not obtained. A maximum pressure ratio of 2.26 was obtained at an equivalent tip speed of 1614 feet per second and an adiabatic efficiency of 0.61. The maximum efficiency obtained was 0.79 at an equivalent tip speed of 801 feet per second and a pressure ratio of 1.29. The performance obtained was considerably below design performance. The effective aerodynamic forces encountered appeared to be large enough to cause considerable damage to the thin aluminum leading edges of the rotor blades.

Physical Description

16 p. : ill.

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  • URL: http://hdl.handle.net/2060/20050019422 External Link
  • Report No.: NACA-RM-SE9G19
  • Center for AeroSpace Information Number: 20050019422
  • Archival Resource Key: ark:/67531/metadc64331

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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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  • 1949

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • June 6, 2018, 10:58 a.m.

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Hartmann, Melvin J. & Tysl, Edward R. Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, 3: Over-All Performance of Compressor, report, 1949; (digital.library.unt.edu/ark:/67531/metadc64331/: accessed October 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.