03456cam a2200481Ia 4500100167864MiAaHDL20250726000000.0m d cr bn ---auaua110426e195701 dcua tb f001 0 eng d(MiU)990128618210106381sdr-miu.990128618210106381(MiU)MIU01000000000000012861821-goog(OCoLC)714797024(MiU)Aleph012861821LHLLHLNACARUtOrBLWNACAY 3.N 21/5:15/E56I04NACA RM E56I04Graves, Charles C.Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas /Charles C. Graves and Jack S. Grobman.Washington, D.C. :National Advisory Committee for Aeronautics,1957.[1], 85 p. :ill. ;27 cm.texttxtrdacontentunmediatednrdamediavolumencrdacarrierNACA research memorandum ;E56I04NACA Research Memorandum E56I04."January 4, 1957."Title from cover.Includes bibliographical references.The combustor total-pressure-loss coefficient and liner air-flow distribution are presented graphically in terms of the following dimensionless parameters: (1) combustor reference Mach number, (2) ratio of combustor-exit to inlet total temperature, (3) fraction of total airflow passing through the liner dome, (4) ratio of total open hole area in liner wall to total combustor cross-sectional area, and (5) ratio of liner cross-sectional area to total combustor cross-sectional area.Compressible and incompressible flow calculations were made of the combustor total-pressure-loss coefficient and liner airflow distribution for tubular turbojet combustors having constant annulus and liner cross-sectional areas along the combustor axis. Information on static and total pressure distribution and liner air-jet entrance angles along the length of the combustor was obtained as an intermediate step in the calculations. The calculations include the effects of heat release, annulus wall friction, and variation in discharge coefficients of the liner wall openings along the combustor.Mode of access: Internet.Charts, diagrams, etc.http://id.loc.gov/authorities/subjects/sh87002373Mathematics.http://id.loc.gov/authorities/subjects/sh85082139Air flow.http://id.loc.gov/authorities/subjects/sh85002635Combustion chambers.http://id.loc.gov/authorities/subjects/sh85028837AirplanesTurbojet engines.http://id.loc.gov/authorities/subjects/sh85002908Grobman, Jack S.Lewis Flight Propulsion Laboratory.http://id.loc.gov/authorities/names/no2015026965http://id.loc.gov/rwo/agents/no2015026965http://viaf.org/viaf/314909134United States.National Adviosry Committee for Aeronautics.NACA research memorandum.United States.National Advisory Committee for Aeronautics.http://id.loc.gov/authorities/names/n79060141http://id.loc.gov/rwo/agents/n79060141Technical Report Archive & Image Library (TRAIL)3901508646397610016786420241218084302.020250726000000.020260307140652.02026-03-08T08:44:01Z2024-04-06T17:30:02ZSDR-MIUmiuALMAprepare.pl-004-009BKsdr-miu.990128618210106381MiUSDRGWLA012861821mdp.39015086463976MIU990128618210106381MIUGWLA20260308googlemdp.390150864639761957pdbibUS fed doc