Special Issue "Recent Advances in SWBLI Research"
A special issue of Aerospace (ISSN 2226-4310).
Deadline for manuscript submissions: 31 January 2015
Dr. Hossein Zare-Behtash
School of Engineering, University of Glasgow, Glasgow G12 8QQ, Scotland, UK
The necessity of traveling faster, whether it concerns travel from country to country, access to space, interplanetary travel, or merely the reduction of environmental impacts (within the aerospace industry), has brought us face to face with a fundamental and unsteady fluid dynamic phenomenon: namely, the Shock Wave–Boundary Layer Interaction (SWBLI) phenomenon. Uncontrolled, SWBLIs can lead to regions of high thermal gradient, structural fatigue and vibrations, fluid–thermal–structure interactions, and losses in propulsive efficiency in transonic and hypersonic vehicles.
Various specialist groups around the world have dedicated many years and extensive numerical and experimental resources to understanding SWBLI, with the ultimate goal of controlling and mitigating its adverse effects. Thus, the phenomenon of SWBLI is a challenging and exciting topic. This drive to understand has produced many advances in our numerical and experimental capabilities within fluid dynamics. These innovations motivate this Special Issue.
We invite papers addressing both the advances in our fundamental understanding of the SWBLI phenomena and also the latest in the numerical and experimental tools and techniques that are currently being utilized for this purpose.
Dr. Hossein Zare-Behtash
Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. Papers will be published continuously (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.
Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are refereed through a peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed Open Access quarterly journal published by MDPI.
Please visit the Instructions for Authors page before submitting a manuscript. For the first couple of issues the Article Processing Charge (APC) will be waived for well-prepared manuscripts. English correction and/or formatting fees of 250 CHF (Swiss Francs) will be charged in certain cases for those articles accepted for publication that require extensive additional formatting and/or English corrections.
The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.
Title: Shock Wave Diffraction Phenomena Around Slotted Splitters
Authors: F. Gnani *, K. H. Lo, H. Zare-Behtash, and K. Kontis
Affiliation:University of Glasgow, School of Engineering, Glasgow G12 8QQ, UK
Abstract: In the field of aerospace engineering the study of the characteristics of vortical flows and their un-steady phenomena finds numerous engineering applications related to improvements in the design of tip devices, enhancement of combustor performance, and control of noise generation. A large amount of work has been carried out in the analysis of the shock wave diffraction around conventional geometries such as sharp and rounded corners, but the employment of splitters with lateral variation has hardly attracted the attention of researchers. The investigation of this phenomenon around two-dimensional wedges has allowed the understanding of the basic physical principles of the flow features. On the other hand, important aspects which appear in the third dimension due to the turbulent nature of the vortices are omitted. The lack of studies which use three-dimensional geometries has motivated the current work to experimentally investigate the evolution of the shock wave diffraction around two splitters with spike-shaped structures for Mach numbers of 1.31 and 1.59. Schlieren photography was used to obtain an insight into the sequential diffraction processes which take place in different planes. Interacting among them, these phenomena generate a complicated turbulent cloud with a vortical arrangement.
Last update: 30 October 2014