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International Journal of Fluid Mechanics Research
ESCI SJR: 0.206 SNIP: 0.446 CiteScore™: 0.9

ISSN Print: 2152-5102
ISSN Online: 2152-5110

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International Journal of Fluid Mechanics Research

DOI: 10.1615/InterJFluidMechRes.v41.i3.10
pages 185-193

Numerical Investigation of Symmetrical Supersonic Inlet with Boundary Layer Suction

Ali Momeny Sarmazdeh
Department of Mechanical Engineering, Iran University of Science and Technology Tehran, Iran
Mojtaba Tahani
Faculty of New Sciences and Technologies, Tehran University, Tehran, Iran
Mohsen Motahari Nezhad
Department of Mechanical Engineering, Iran University of Science and Technology Tehran, Iran

ABSTRACT

In this study, an input stream of symmetrical supersonic inlet with boundary layer suction has been investigated by using of two-dimensional full Navier−Stokes equations. The analysis has been performed for three various Mach numbers. The main purpose of this study is reduction of adverse pressure gradient for performance improvement of supersonic air-intake. At this paper, the upper leading edge has been considered round because the sharp leading edge cannot withstand the high thermal loading in supersonic flow. The results show that the high pressure gradient across the crossing shock waves has been minimized by the use of boundary layer suction. So, the input mass flow rate to air-intake has been increased. Viscose and non-viscose Turbulent flow analysis has been done by McCormack explicit method. Modeling of turbulent flow has been done with Wilcox k-ω two equations model. The results have been compared with the prestigious experimental papers at the end.


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