A new approach for the design of hypersonic scramjet inlets

N, Om Prakash Raj and K, Venkatasubbaiah (2012) A new approach for the design of hypersonic scramjet inlets. Physics of Fluids, 24 (8). 086103-1. ISSN 1070-6631

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A new methodology has been developed for the design of hypersonic scramjet inlets using gas dynamic relations. The approach aims to find the optimal inlet geometry which has maximum total pressure recovery at a prescribed design free stream Mach number. The design criteria for inlet is chosen as shock-on-lip condition which ensures maximum capture area and minimum intake length. Designed inlet geometries are simulated using computational fluid dynamics analysis. The effects of 1D, 2D inviscid and viscouseffects on performance of scramjet inlet are reported here. A correction factor in inviscid design is reported for viscouseffects to obtain shock-on-lip condition. A parametric study is carried out for the effect of Mach number at the beginning of isolator for the design of scramjet inlets. Present results show that 2D and viscouseffects are significant on performance of scramjet inlet. Present simulation results are matching very well with the experimental results available from the literature.

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IITH Creators:
IITH CreatorsORCiD
K, VenkatasubbaiahUNSPECIFIED
Item Type: Article
Subjects: Physics > Fluid mechanics
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Divisions: Department of Mechanical & Aerospace Engineering
Depositing User: Users 3 not found.
Date Deposited: 22 Sep 2014 09:54
Last Modified: 25 Mar 2015 07:35
URI: http://raiith.iith.ac.in/id/eprint/39
Publisher URL: http://dx.doi.org/10.1063/1.4748130
OA policy: http://www.sherpa.ac.uk/romeo/issn/1070-6631/
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