Output details
15 - General Engineering
University of Liverpool
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Output 0 of 0 in the submission
Article title
Shock Effects on Delta Wing Vortex Breakdown
Type
D - Journal article
DOI
Title of journal
Journal of Aircraft
Article number
-
Volume number
46
Issue number
3
First page of article
903
ISSN of journal
1533-3868
Year of publication
2009
URL
-
Number of additional authors
5
Additional information
This work formed part of a NATO scientific working group (Applied Vehicle Technology - 113) and describes a computational study into the previously unexplained physical mechanism behind the slender wing vortex breakdown behaviour observed in a transonic wind tunnel test at NASA. Work exploiting the validated method, on complex vortical flow interactions relevant to unmanned air vehicle stability and control, is being done in the Technology Strategy Board SimOD project (evidence file Badcock3-1.pdf).
Interdisciplinary
-
Cross-referral requested
-
Research group
None
Proposed double-weighted
No
Double-weighted statement
-
Reserve for a double-weighted output
No
Non-English
No
English abstract
-
