Vortical flow prediction validation for an unmanned combat air vehicle model
Vortical flow prediction validation for an unmanned combat air vehicle model
As part of the NATO Applied Vehicle Technology 161 technical group, a study of the aerodynamic behavior of the stability and control configuration wind-tunnel model is presented. Sharp and round leading-edge versions of the model are computed. A validation of Reynolds-averaged Navier–Stokes predictions obtained using two block structured codes are made. Static cases are analyzed and compared with wind-tunnel measurements. The vortical flow features are described in detail for a range of angles of attack. The predictions are in good agreement with the experiments at low angles of attack, whereas for higher angles of incidence (alpha > 15), some discrepancies are seen. A dual vortex structure is present in this region for both leading-edge configurations, resulting in highly nonlinear aerodynamic behavior.
1948-1959
Vallespin, D.
b979d052-a22b-4b46-8578-2fb851b7e174
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Boelens, O.
878276fe-5da3-40f3-90e6-1c33371d8a21
Badcock, K. J.
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November 2011
Vallespin, D.
b979d052-a22b-4b46-8578-2fb851b7e174
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Boelens, O.
878276fe-5da3-40f3-90e6-1c33371d8a21
Badcock, K. J.
64c4dc5d-1f2f-4358-af31-f6506c1810ef
Vallespin, D., Da Ronch, A., Boelens, O. and Badcock, K. J.
(2011)
Vortical flow prediction validation for an unmanned combat air vehicle model.
Journal of Aircraft, 48 (6), .
(doi:10.2514/1.C031385).
Abstract
As part of the NATO Applied Vehicle Technology 161 technical group, a study of the aerodynamic behavior of the stability and control configuration wind-tunnel model is presented. Sharp and round leading-edge versions of the model are computed. A validation of Reynolds-averaged Navier–Stokes predictions obtained using two block structured codes are made. Static cases are analyzed and compared with wind-tunnel measurements. The vortical flow features are described in detail for a range of angles of attack. The predictions are in good agreement with the experiments at low angles of attack, whereas for higher angles of incidence (alpha > 15), some discrepancies are seen. A dual vortex structure is present in this region for both leading-edge configurations, resulting in highly nonlinear aerodynamic behavior.
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Published date: November 2011
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 351512
URI: http://eprints.soton.ac.uk/id/eprint/351512
ISSN: 0021-8669
PURE UUID: ecff6346-e4a8-44f6-89e7-80c62afb2ba4
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Date deposited: 23 Apr 2013 12:11
Last modified: 15 Mar 2024 03:46
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Author:
D. Vallespin
Author:
O. Boelens
Author:
K. J. Badcock
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