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ENCIT 2020
18th Brazilian Congress of Thermal Sciences and Engineering
INFLUENCE OF THE BOUNDARY LAYER ON THE DESIGN OF THE COMPRESSION SECTION OF A GENERIC SCRAMJET
Submission Author:
Ramon Carneiro , RN
Co-Authors:
Ramon Carneiro, Pedro Paulo Batista de Araújo, Gilvan Borba, George Marinho, Paulo Toro
Presenter: Ramon Carneiro
doi://10.26678/ABCM.ENCIT2020.CIT20-0805
Abstract
The high potential of the scramjet technology to be used in aerospace vehicles has attracted worldwide attention for studies about hypersonic air-breathing propulsion based on supersonic combustion. A key parameter in projects with scramjets is the compression section design. The atmospheric air flow must be compressed to necessaries conditions for supersonic combustion and auto-ignition of the fuel in the combustion chamber. In this work, a theoretical analytical approach was applied to evaluate the thickness and the influence of the boundary layer on the surface of a scramjet projected to fly at an altitude of 30 km with a Mach number equal to 6.8. The geometry of the inlet is based on a compression system composed of three flat compression ramps with deflection angles respectively θ1 = 5.5°; θ2 = 7.0°; θ3 = 8.5°. Computational routines were developed to dimension the thickness of the boundary layer above the three compression ramps using a methodology based on Chapman-Rubesin theory. The results showed that the presence of the boundary layer changed the angles of the incident plane oblique shock waves and, consequently, affects the flow thermodynamic properties like temperature, pressure, density, velocity, and causing air leakage close to the leading edge of the cowl.
Keywords
Scramjet, hypersonic airbreathing propulsion, supersonic combustion, Boundary Layer
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