Computational model for the calculation of the flow about wings with leading-edge vortices

H. W.M. Hoeijmakers, B. Bennekers

Research output: Contribution to journalConference articleAcademicpeer-review

Abstract

A Computational method is presented for the calculation of the incompressible flow about wings with leading-edge vortices. The mathematical model replaces the spiralling free shear layer springing from the leading edge by a free vortex sheet which is terminated by a combination of a feeding sheet plus a discrete line vortex/sink. The strength of the sink is related to the entrainment of the rotational core and derived here from semi-empirical arguments. The resulting potential flow problem is solved employing a higher-order panel method which involves some recently developed ideas for obtaining a numerically efficient method with second-order accuracy. The method is applied to the calculation of the flow about a delta wing at incidence.

Original languageEnglish
JournalAGARD Conference Proceedings
Issue number247
Publication statusPublished - 1 Jan 2017
EventSymposium on High-Angle-of-Attack Aerodynamics 1978 - Sandefjord, Norway
Duration: 4 Oct 19786 Oct 1978

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Vortex flow
Potential flow
Incompressible flow
Computational methods
Mathematical models

Cite this

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title = "Computational model for the calculation of the flow about wings with leading-edge vortices",
abstract = "A Computational method is presented for the calculation of the incompressible flow about wings with leading-edge vortices. The mathematical model replaces the spiralling free shear layer springing from the leading edge by a free vortex sheet which is terminated by a combination of a feeding sheet plus a discrete line vortex/sink. The strength of the sink is related to the entrainment of the rotational core and derived here from semi-empirical arguments. The resulting potential flow problem is solved employing a higher-order panel method which involves some recently developed ideas for obtaining a numerically efficient method with second-order accuracy. The method is applied to the calculation of the flow about a delta wing at incidence.",
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Computational model for the calculation of the flow about wings with leading-edge vortices. / Hoeijmakers, H. W.M.; Bennekers, B.

In: AGARD Conference Proceedings, No. 247, 01.01.2017.

Research output: Contribution to journalConference articleAcademicpeer-review

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N2 - A Computational method is presented for the calculation of the incompressible flow about wings with leading-edge vortices. The mathematical model replaces the spiralling free shear layer springing from the leading edge by a free vortex sheet which is terminated by a combination of a feeding sheet plus a discrete line vortex/sink. The strength of the sink is related to the entrainment of the rotational core and derived here from semi-empirical arguments. The resulting potential flow problem is solved employing a higher-order panel method which involves some recently developed ideas for obtaining a numerically efficient method with second-order accuracy. The method is applied to the calculation of the flow about a delta wing at incidence.

AB - A Computational method is presented for the calculation of the incompressible flow about wings with leading-edge vortices. The mathematical model replaces the spiralling free shear layer springing from the leading edge by a free vortex sheet which is terminated by a combination of a feeding sheet plus a discrete line vortex/sink. The strength of the sink is related to the entrainment of the rotational core and derived here from semi-empirical arguments. The resulting potential flow problem is solved employing a higher-order panel method which involves some recently developed ideas for obtaining a numerically efficient method with second-order accuracy. The method is applied to the calculation of the flow about a delta wing at incidence.

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