Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

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The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a_ flight Mach number of ... continued below

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Groesbeck, Donald E. & Peters, Daniel J. July 28, 1958.

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  • Main Title: Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6
  • Series Title: NACA Research Memorandums

Description

The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a_ flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40. However, further reduction in the afterburner-inlet pressure severely affected combustion efficiency. For example, at an afterburner inlet pressure level of 700 to 1000 pounds per square foot absolute, the efficiency for both configurations was 0.20 to 0.40.

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  • URL: http://hdl.handle.net/2060/20090026526 External Link
  • Report No.: NACA-RM-SE58G01
  • Center for AeroSpace Information Number: 20090026526
  • Archival Resource Key: ark:/67531/metadc65564

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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

  • July 28, 1958

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 30, 2017, 7:27 p.m.

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Groesbeck, Donald E. & Peters, Daniel J. Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6, report, July 28, 1958; (digital.library.unt.edu/ark:/67531/metadc65564/: accessed December 12, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.