Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Connors, James F.; Woollett, Richard R.

Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

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Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 ... continued below

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28 p. : ill.

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Connors, James F. & Woollett, Richard R. August 11, 1952.

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

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Lewis Flight Propulsion Laboratory National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab

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Main Title: Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85
Series Title: NACA Research Memorandums

Description

Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 degrees.

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28 p. : ill.

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English

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Accession or Local Control No: 93R16525
URL: http://hdl.handle.net/2060/19930087235 External Link
Report No.: NACA-RM-E52F04
Center for AeroSpace Information Number: 19930087235
Archival Resource Key: ark:/67531/metadc59338

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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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August 11, 1952

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Nov. 17, 2011, 10:13 p.m.

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April 9, 2018, 5:41 p.m.

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Connors, James F. & Woollett, Richard R. Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85, report, August 11, 1952; (digital.library.unt.edu/ark:/67531/metadc59338/: accessed February 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

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