A new approach for the design of hypersonic scramjet inlet

Prakash Raj, N. O. and Venkatasubbaiah, K (2020) A new approach for the design of hypersonic scramjet inlet. American Institute of Physics Inc..

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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 viscous effects on performance of scramjet inlet are reported here. A correction factor in inviscid design is reported for viscous effects 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 viscous effects 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
Venkatasubbaiah, Khttps://orcid.org/0000-0001-9841-2123
Item Type: Other
Uncontrolled Keywords: hypersonic scramjet inlets.
Subjects: Others > Mechanics
Social sciences > Anthropology
Physics > Modern physics
Divisions: Department of Mechanical & Aerospace Engineering
Depositing User: . LibTrainee 2021
Date Deposited: 17 Jul 2021 06:56
Last Modified: 18 Nov 2022 05:05
URI: http://raiith.iith.ac.in/id/eprint/8392
Publisher URL: http://doi.org/10.1063/5.0012513
OA policy: https://v2.sherpa.ac.uk/id/publication/9872
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