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Indraft supersonic wind tunnel for shock train investigations

Indraft supersonic wind tunnel for shock train investigations
Indraft supersonic wind tunnel for shock train investigations
The study of the shock wave structure which forms in a nearly constant-area duct is particularly relevant for the prediction and control of shock waves interacting with the boundary-layer in air-breathing engine inlets. The present paper examines the flow physics characterising the shock wave structure, referred to as shock train or pseudo-shock, which forms inside a duct. The parameters which need to be considered in the design of an indraft supersonic wind tunnel are also considered. The facility under consideration has been designed to reproduce the compressibility effects developed by shock trains for Mach numbers between 2 and 4.
1407-1411
Springer Cham
Gnani, F.
6001364a-f3ee-400e-9394-8adb273c044a
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
e40ecdbc-e5e9-4522-abf9-e3c3f3c2d7fa
Ben-Dor, G.
Sadot, O.
Igra, O.
Gnani, F.
6001364a-f3ee-400e-9394-8adb273c044a
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
e40ecdbc-e5e9-4522-abf9-e3c3f3c2d7fa
Ben-Dor, G.
Sadot, O.
Igra, O.

Gnani, F., Zare-Behtash, H. and Kontis, K. (2017) Indraft supersonic wind tunnel for shock train investigations. Ben-Dor, G., Sadot, O. and Igra, O. (eds.) In 30th International Symposium on Shock Waves 2. Springer Cham. pp. 1407-1411 . (doi:10.1007/978-3-319-44866-4_107).

Record type: Conference or Workshop Item (Paper)

Abstract

The study of the shock wave structure which forms in a nearly constant-area duct is particularly relevant for the prediction and control of shock waves interacting with the boundary-layer in air-breathing engine inlets. The present paper examines the flow physics characterising the shock wave structure, referred to as shock train or pseudo-shock, which forms inside a duct. The parameters which need to be considered in the design of an indraft supersonic wind tunnel are also considered. The facility under consideration has been designed to reproduce the compressibility effects developed by shock trains for Mach numbers between 2 and 4.

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More information

e-pub ahead of print date: 2 August 2017

Identifiers

Local EPrints ID: 493588
URI: http://eprints.soton.ac.uk/id/eprint/493588
PURE UUID: 8a25d338-27a0-4af9-860e-246c93723100
ORCID for H. Zare-Behtash: ORCID iD orcid.org/0000-0002-4769-4076

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Date deposited: 09 Sep 2024 16:30
Last modified: 10 Sep 2024 02:10

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Contributors

Author: F. Gnani
Author: H. Zare-Behtash ORCID iD
Author: K. Kontis
Editor: G. Ben-Dor
Editor: O. Sadot
Editor: O. Igra

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