Flight investigation of the cooling characteristics of a two-row radial engine installation III : engine temperature distribution

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The temperature distribution of a two-row radial engine in a twin-engine airplane has been investigated in a series of flight tests. The test engine was operated over a wide range of conditions at density altitudes of 5000 and 20,000 feet; quantitative results are presented showing the effects of flight and engine variables upon average engine temperature and over-all temperature spread. Discussions of the effect of the variables on the shape of the temperature patterns and on the temperature distribution of individual cylinders are also included. The results indicate that, for the tests conducted, the temperature distribution patterns were chiefly determined ... continued below

Creation Information

Rennak, Robert M; Messing, Wesley E & Morgan, James E October 1, 1946.

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  • Main Title: Flight investigation of the cooling characteristics of a two-row radial engine installation III : engine temperature distribution
  • Series Title: NACA Technical Notes

Description

The temperature distribution of a two-row radial engine in a twin-engine airplane has been investigated in a series of flight tests. The test engine was operated over a wide range of conditions at density altitudes of 5000 and 20,000 feet; quantitative results are presented showing the effects of flight and engine variables upon average engine temperature and over-all temperature spread. Discussions of the effect of the variables on the shape of the temperature patterns and on the temperature distribution of individual cylinders are also included. The results indicate that, for the tests conducted, the temperature distribution patterns were chiefly determined by the fuel-air ratio and cooling-air distributions. It was possible to calculate individual cylinder temperature, on the assumption of equal power distribution among cylinders, to within an average of plus or minus 14 degrees F. of the actual temperature. A considerable change occurred in either the spread or the thrust axis, the average engine fuel-air ratio, the engine speed, the power, or the blower ratio. Smaller effects on the temperature pattern were noticed with a change in cowl-flap opening and altitude. In most of the tests, a change in conditions affected the temperature of the barrels less than that of the heads. The variation of flight and engine variables had a negligible effect on the temperature distributions of the individual cylinders. (author).

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  • : 93R11103
  • URL: http://hdl.handle.net/2060/19930081813 External Link
  • Report No.: NACA-TN-1147
  • Center for AeroSpace Information Number: 19930081813
  • Archival Resource Key: ark:/67531/metadc55053

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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

  • October 1, 1946

Added to The UNT Digital Library

  • Nov. 14, 2011, 10:28 p.m.

Description Last Updated

  • Feb. 2, 2017, 12:39 p.m.

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Rennak, Robert M; Messing, Wesley E & Morgan, James E. Flight investigation of the cooling characteristics of a two-row radial engine installation III : engine temperature distribution, report, October 1, 1946; (digital.library.unt.edu/ark:/67531/metadc55053/: accessed August 23, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.