Quantitative comparison of 2D and 3D shock control bumps for drag reduction on transonic wings

Deng, F. and Qin, N. orcid.org/0000-0002-6437-9027 (2018) Quantitative comparison of 2D and 3D shock control bumps for drag reduction on transonic wings. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 233 (7). pp. 2344-2359. ISSN 0954-4100

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Copyright, Publisher and Additional Information: © 2018 IMechE. This is an author-produced version of a paper subsequently published in Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. Uploaded in accordance with the publisher's self-archiving policy.
Keywords: Drag reduction; flow control; natural laminar flow; shock control bump; transonic
Dates:
  • Accepted: 23 April 2018
  • Published (online): 29 May 2018
  • Published: 1 June 2018
Institution: The University of Sheffield
Academic Units: The University of Sheffield > Faculty of Engineering (Sheffield) > Department of Mechanical Engineering (Sheffield)
Depositing User: Symplectic Sheffield
Date Deposited: 16 Dec 2019 14:06
Last Modified: 16 Dec 2019 14:11
Status: Published
Publisher: SAGE Publications
Refereed: Yes
Identification Number: https://doi.org/10.1177/0954410018778815
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