Experimental and complementary CFD results from the study of the rocket-ejector mode of a Rocket Based Combined Cycle (RBCC) engine are presented and discussed. The experiments involved systematic flowfield measurements in a two-dimensional, variable geometry rocket-ejector system. The rocket-ejector system utilizes a single two-dimensional, gaseous oxygen/gaseous hydrogen rocket as the ejector. To gain a thorough understanding of the rocket-ejector's internal fluid mechanic/combustion phenomena, experiments were conducted with both direct-connect and sea-level static configurations for a range of rocket operating conditions. Overall system performance was obtained through global measurements of wall static pressure profiles, heat flux profiles and engine thrust, whereas detailed mixing and combustion information was obtained through Raman spectroscopy measurements of major species (oxygen, hydrogen, nitrogen and water vapor). The experimental results for both the direct-connect and sea-level static configurations are compared with CFD predictions of the flowfield.
Experiment/Analytical Characterization of the RBCC Rocket-Ejector Mode
2000
9 pages
Report
No indication
English
Fluid Mechanics , Computational fluid dynamics , Ejectors , Rocket-based combined-cycle engines , Spacecraft propulsion , Algorithms , Computational grids , Boundary conditions , Static pressure , Flow distribution , Fluid mechanics , Pressure distribution , Wall pressure , Combustion physics , Raman spectroscopy
Focused Experimental and Analytical Studies of the RBCC Rocket-Ejector Mode
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British Library Conference Proceedings | 2000
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