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This research evaluates the combustion behaviors of a single-element, swirl-coaxial injector in an atmospheric combustion chamber with gaseous oxygen and gaseous hydrogen (GO2/GH2) as the propellants. A brief simulated flow field schematic comparison between a shear-coaxial injector and the swirl-coaxial injector reveals the distribution characteristics of the temperature field and streamline patterns...
Estimation the temperature distribution on nozzle wall by predicting the thermal environment is most important for assessing the life of the nozzle. For that purpose, the coupling simulation of the conjugate heat transfer and transient temperature on the rocket nozzle wall is studied. The equation of radiative heat flux on surfaces of an enclosure filled with inhomogeneous, participating media is...
Calculation of the infrared characteristics of a rocket nozzle is very important for the study of infrared initiating technology. The Narrow-Band Zone model is developed for that purpose. The spectral transmission and absorption factors are introduced, and the equations between radiative heat flux and the temperature of wall surfaces and gas are developed. The radiative heat transfer in one axisymmetric...
Flow field numerical simulation methods of scramjet introduced in this paper, include using CFD method to analyze the flow phenomenon in each component of scramjet, i.e. forebody/inlet, combustor and afterbody/nozzle. Design and optimization of a generic scramjet model are investigated based on the bilevel integrated system synthesis method. Analysis and design procedures of each component are treated...
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