Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder

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Several methods of predicting the compressible-flow pressure loss across a baffled aircraft-engine cylinder were analytically related and were experimentally investigated on a typical air-cooled aircraft-engine cylinder. Tests with and without heat transfer covered a wide range of cooling-air flows and simulated altitudes from sea level to 40,000 feet. Both the analysis and the test results showed that the method based on the density determined by the static pressure and the stagnation temperature at the baffle exit gave results comparable with those obtained from methods derived by one-dimensional-flow theory. The method based on a characteristic Mach number, although related analytically to … continued below

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375 - 389 p. : ill.

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Neustein, Joseph & Schafer, Louis J., Jr. October 9, 1945.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided by the UNT Libraries Government Documents Department to the UNT Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 161 times. More information about this report can be viewed below.

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  • Main Title: Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder
  • Series Title: NACA Technical Reports

Description

Several methods of predicting the compressible-flow pressure loss across a baffled aircraft-engine cylinder were analytically related and were experimentally investigated on a typical air-cooled aircraft-engine cylinder. Tests with and without heat transfer covered a wide range of cooling-air flows and simulated altitudes from sea level to 40,000 feet. Both the analysis and the test results showed that the method based on the density determined by the static pressure and the stagnation temperature at the baffle exit gave results comparable with those obtained from methods derived by one-dimensional-flow theory. The method based on a characteristic Mach number, although related analytically to one-dimensional-flow theory, was found impractical in the present tests because of the difficulty encountered in defining the proper characteristic state of the cooling air. Accurate predictions of altitude pressure loss can apparently be made by these methods, provided that they are based on the results of sea-level tests with heat transfer.

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375 - 389 p. : ill.

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  • Accession or Local Control No: 93R21220
  • URL: http://hdl.handle.net/2060/19930091930 External Link
  • Report No.: NACA-TR-858
  • Center for AeroSpace Information Number: 19930091930
  • Archival Resource Key: ark:/67531/metadc60153

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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 9, 1945

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • April 9, 2018, 2:26 p.m.

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Neustein, Joseph & Schafer, Louis J., Jr. Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder, report, October 9, 1945; (https://digital.library.unt.edu/ark:/67531/metadc60153/: accessed May 18, 2025), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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