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ENCIT 2020
18th Brazilian Congress of Thermal Sciences and Engineering
NUMERICAL ANALYSIS OF THE AERODYNAMIC PERFORMANCE OF A ROCKET ENGINE COUPLED TO A SCRAMJET DEMONSTRATOR
Submission Author:
Felipe Pinheiro Maia , RN
Co-Authors:
Felipe Pinheiro Maia, Sandi Souza, Thiago Cardoso de Souza
Presenter: Felipe Pinheiro Maia
doi://10.26678/ABCM.ENCIT2020.CIT20-0230
Abstract
In this work we analyze the effect of the coupling of a scramjet demonstrator in a brazilian rocket engine in terms of a numerical investigation of the flow around its fuselage geometry. We consider local aspects of the flow and the comparison of global flow parameters, such as the pressure and friction drag, in both geometries. The rocket engine geometry is the brazilian S-30, with the VS-30 rocket as the reference geometry, while the scramjet geometry was selected for operational flight conditions of a Mach number equal to 5.79 and an altitude of 20 km. A set of 2D axisymmetric and planar numerical domains were generated for both geometries. We consider steady-state conditions in all cases, and for the modelling of the turbulent flow, the transition k-kl-ω viscous model was applied. The simulations were able to capture the theoretically expected conical oblique shock and the expansions waves that usually occur for a hypersonic past such geometries. Local effects in the flow were observed such as the emergence of recirculation zones and flow instabilities due to the shock-wave boundary layer interactions. Finally, as a result of the coupling of the scramjet demonstrator to the S-30 rocket engine, the results show an increase in the total drag of about 6.53%.
Keywords
Scramjet, VS-30, Shock-Wave Boundary Layer Interactions, Hypersonic Flow, Drag
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