Numerical studies of the automatic control of Boundary-Layer transition via multiple suction panels
Numerical studies of the automatic control of Boundary-Layer transition via multiple suction panels
A numerical algorithm is introduced for the optimization of the suction distribution to maintain transition at a desired position for a flow over a flat plate with a smooth two-dimensional hump and an array of suction panels. The computation consists of the calculation of the interacting boundary-layer flow, the determination of the spatial growth rates of the disturbance waves, the prediction of the transition location via the eN-method and finally of the optimization of the suction flow rates using a modified least mean-squares algorithm. The optimization algorithm has been successfully applied to plates with two or four suction panels. The results show clearly that the pressure distribution has a highly significant effect on the optimum suction distribution over the plate. The numerical code shows its potential to be applied to laminar flow control aerofoils to determine the optimum suction distribution for given flight conditions.
Hackenberg, P.
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Tutty, O. R.
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Nelson, P. A.
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23 June 1994
Hackenberg, P.
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Tutty, O. R.
c9ba0b98-4790-4a72-b5b7-09c1c6e20375
Nelson, P. A.
5c6f5cc9-ea52-4fe2-9edf-05d696b0c1a9
Hackenberg, P., Tutty, O. R. and Nelson, P. A.
(1994)
Numerical studies of the automatic control of Boundary-Layer transition via multiple suction panels.
AIAA Fluid Dynamics Conference, 1994, , Colorado Springs, United States.
20 - 23 Jun 1994.
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Conference or Workshop Item
(Paper)
Abstract
A numerical algorithm is introduced for the optimization of the suction distribution to maintain transition at a desired position for a flow over a flat plate with a smooth two-dimensional hump and an array of suction panels. The computation consists of the calculation of the interacting boundary-layer flow, the determination of the spatial growth rates of the disturbance waves, the prediction of the transition location via the eN-method and finally of the optimization of the suction flow rates using a modified least mean-squares algorithm. The optimization algorithm has been successfully applied to plates with two or four suction panels. The results show clearly that the pressure distribution has a highly significant effect on the optimum suction distribution over the plate. The numerical code shows its potential to be applied to laminar flow control aerofoils to determine the optimum suction distribution for given flight conditions.
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Published date: 23 June 1994
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© 1994 by the American Institute of Aeronautics and Astronautics, Inc. All right reserved.
Paper number : AIAA 94-2214
Venue - Dates:
AIAA Fluid Dynamics Conference, 1994, , Colorado Springs, United States, 1994-06-20 - 1994-06-23
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Local EPrints ID: 468797
URI: http://eprints.soton.ac.uk/id/eprint/468797
PURE UUID: a84f837d-e9d3-4849-a9e5-3bae6892058b
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Date deposited: 25 Aug 2022 17:22
Last modified: 26 Aug 2022 01:32
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Author:
P. Hackenberg
Author:
O. R. Tutty
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