Nozzle geometry effects on corner boundary layers in supersonic wind tunnels
Accepted version
Peer-reviewed
Repository URI
Repository DOI
Change log
Authors
Sabnis, Kshitij https://orcid.org/0000-0001-7609-2923
Babinsky, Holger https://orcid.org/0000-0002-7647-7126
Abstract
Experiments on supersonic flows are typically conducted in wind tunnels with rectangular cross-sections, which use two-dimensional nozzles of two different types. A “full” setup consists of two contoured nozzle surfaces symmetric about the tunnel centre-height. The “half” configuration is also common, with a curved ceiling nozzle surface and a straight horizontal floor.
Description
Keywords
4012 Fluid Mechanics and Thermal Engineering, 40 Engineering, 4001 Aerospace Engineering
Journal Title
AIAA Journal
Conference Name
Journal ISSN
0001-1452
1533-385X
1533-385X
Volume Title
57
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Publisher DOI
Rights
All rights reserved
Sponsorship
Air Force Research Laboratory
UK National Wind Tunnel Facility