High-Frequency Combustion Instability in Rocket Motor with Concentrated Combustion

Nomenclature ® — absolute value of the angular frequencj' = <o(6/2) 7 == adiabatic index of the combustion gas <p = p exp ( — at) 5 = p' exp ( — at) v = u' exp ( — at) £ = dimensionless distance of the concentrated combustion front from the injector end expressed as a fraction of the characteristic length L (3 — reduced angular frequency of the oscillation = angular frequency divided by the velocity gradient in de Laval nozzle z = reduced velocity parameter = u 4l ) / 2