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Data are presented to show the effects of inlet-air pressure, inlet-air temperature, and compression ratio on the maximum permissible performance obtained with a cylinder having a hemispherical-dome combustion chamber. The five aircraft engine fuels used have octane number varying from 90 to 100 plus 2 ml of tetraethyl lead per gallon. The results for each fule can be correlated by plotting the calculated end-gas density factor against the calculated end-gas temperature. Measurements of spark-plug electrode temperatures showed thta, with two spark plugs, cutting off the switch to one spark plug lowered the electrode temperature of that plug from a value of 1,365 degrees F to a value of 957 degrees F. The results indicate that the surface temperatures of combustion-chamber areas which become new sources of ignitiion markedly increase after ignition commences.
Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
Reproductions of reports, some declassified, of research done at Aircraft Engine Research Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
This report presents the results of an investigation on the distribution of stress in a plate elastically supported along two edges and subjected to compressive loads in a direction parallel to the elastically supported edges.
The NACA and aircraft propulsion, 1915-1958 -- NASA gets to work, 1958-1975 -- The shift toward commercial aviation, 1966-1975 -- The quest for propulsive efficiency, 1976-1989 -- Propulsion control enters the computer era, 1976-1998 -- Transiting to a new century, 1990-2008 -- Toward the future