Accession Number : AD0747030

Title :   Supersonic Combustion and Burning in Ramjet Combustors,

Corporate Author : OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS

Personal Author(s) : Edse,Rudolph ; Neer,Michael ; Scott,N. ; Strauss,W. A.

Report Date : 12 JUN 1972

Pagination or Media Count : 42

Abstract : The report discusses research results obtained on the experimental and theoretical studies of subsonic and supersonic burning in ramjet combustors during the period 1 April to 31 March 1972. During this period theoretical calculations showed that nozzle dimensions for a chemically reacting flow must be based on the shifting equilibrium sound speed. Incompatible conditions are obtained when the frozen sound speed is used. The difference in the nozzle area for the two cases is significant. Deviations of the observed wave speed and pressure of detonations in hydrogen-oxygen and hydrogen-nitric oxide mixtures initially at high pressure from the theoretical values were determined to be caused apparently by turbulence in the gas flow behind the wave. (Author)

Descriptors :   (*SUPERSONIC COMBUSTION RAMJET ENGINES, SUPERSONIC COMBUSTION), SUPERSONIC NOZZLES, NOZZLE AREA RATIO, CHARGED PARTICLES, COMBUSTION CHAMBERS, SHIFTING EQUILIBRIUM FLOW, FROZEN EQUILIBRIUM FLOW, IGNITION

Subject Categories : Combustion and Ignition
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE