A Higher-order panel method for the computation of the flow about slender delta wings with leading-edge vortex separation

Title

A Higher-order panel method for the computation of the flow about slender delta wings with leading-edge vortex separation

 Author

Hoeijmakers, H.W.M.
Vaatstra, W.

Institution

National Aerospace Laboratory NLR

 Date

1981-09-05

 Abstract

For the limiting cases of conical flow about delta wings and time dependent 2-D development of the wake behind the trailing edge of wings a new second-order panel method is described. It is demonstrated that the panel method is stable for the mixed design/analysis boundary conditions characterizing both problems. The method for following 2-D vortex sheet motion includes an adaptive curvature-dependent panel scheme and a concept for doubly-branched spiralling vortices, which enables the motion of vortex sheets of complicated shape to be followed up to large downstream distances. Conical flow results are presented for different angles of attack and for different cross-sectional shapes. Vortex sheet roll-up results are presented for the wake behind a flat delta wing.

 To reference this document use:

http://resolver.tudelft.nl/uuid:da4f447b-3f40-4868-8722-8030d37e73ed

 Publisher

Nationaal Lucht- en Ruimtevaartlaboratorium

 Access restriction

Campus only

 Source

NLR MP 81053 U

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

(c) 1981 National Aerospace Laboratory NLR
Files
PDF 81053.pdf 8.25 MB
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