Performance Enhancement of a Supersonic Air Intake by Applying a Heat Source
Publication: Journal of Aerospace Engineering
Volume 33, Issue 5
Abstract
The main objective of this paper is to study the effects of applying a heat source ahead of a supersonic mixed compression air intake. This intake has been designed for the freestream Mach number 2. Four parameters of the heat source, including its location, cross-sectional shape, cross-sectional area, and heat generation rate, are investigated numerically to find a suitable heat source that enhances the performance of the intake. The research is conducted at the freestream Mach numbers of 1.8, 2, and 2.2. Total pressure recovery, mass flow ratio, flow distortion, and drag coefficient are considered as the intake performance parameters. Variation of the critical backpressure is further investigated. The results show that a bow shock is formed around the heat source that affects the intake shock system and can have desirable effects on most of the performance parameters and the critical backpressure at different freestream Mach numbers. It is also observed that the heat source location is the most effective parameter of the heat source, and should be selected meticulously.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
This study was financially supported by Ferdowsi University of Mashhad (FUM), Iran (Grant No. 46236).
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Information
Published In
Journal of Aerospace Engineering
Volume 33 • Issue 5 • September 2020
Copyright
©2020 American Society of Civil Engineers.
History
Received: Aug 27, 2019
Accepted: Mar 9, 2020
Published online: May 30, 2020
Published in print: Sep 1, 2020
Discussion open until: Oct 30, 2020
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