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ArticlePeer ReviewedOpen AccessPlagiarism Passed
Paper ID:10.55041/IJSREM15312

Computational Study of Hypersonic Scramjet Experimental Vehicle Intake

Stream/Area:

-

Subject:

-

Paper ID:

10.55041/IJSREM15312

Volume:

6 |

7 |

Jul 2022

Pages:

Publication Frequency:

Monthly (12 issues per year)

DOI
Digital Object Identifier
10.55041/IJSREM15312

License:International Journal of Scientific Research in Engineering and Management follows the Creative Commons Attribution 4.0 (CC BY 4.0) License, allowing free use and distribution with proper attribution.

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Authors

APD

Ashvini P Desai

KJR

Keziya J R

MD

Melini D

NMG

Nihal Moni George

PA

Premkumar A

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Abstract

To design an efficient intake for a scramjet engine which can be operated in hypersonic conditions between Mach 6 and 7. A computational fluid dynamics analysis is performed on the intake design to analyze its pressure losses, shocks and the possibility of flow separation. The intake of the scramjet engine is designed for critical Mach number of 6.5.

KEYWORDS

Scramjet inlet Ramp angle Ramp length Cowl Oblique shock ANSYS Hypermesh.

Cite This Article

Ashvini P Desai, Keziya J R, Melini D, Nihal Moni George, Premkumar A, "Computational Study of Hypersonic Scramjet Experimental Vehicle Intake," International Journal of Scientific Research in Engineering and Management, vol. 6, no. 7, Jul 2022. https://doi.org/10.55041/IJSREM15312

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Publication Date

3/6/2022

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Review Rounds: 2

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The authors declare no conflict of interest related to this research work.

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