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A numerical model for analysis of thin wings in inviscid incompressible flow

Published online by Cambridge University Press:  04 July 2016

B. K. Singh  and
B. C. Basu
B. K. Singh
Affiliation:
Department of Aeronautical Engineering, Indian Institute of Technology, Kharagpur, India
B. C. Basu
Affiliation:
Department of Aeronautical Engineering, Indian Institute of Technology, Kharagpur, India
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Summary

A planar vortex sheet model for analysis of thin wings in inviscid incompressible flow is presented. In this model a network of spanwise quadratically varying semi-infinite doublet sheets is introduced which produces a continuous trailing vortex wake. The present method has been applied to wings fitted with partial span trailing edge flaps after appropriate modification to account for the flap juncture. Also, the problem of wings in sideslip is attempted by incorporating the zero load condition at the down stream wing tip. The comparison of results shows that the proposed model retains the simplicity of the vortex lattice model to a large extent while overcoming the limitations of the standard vortex lattice model regarding lattice arrangement and number.

Type
Research Article
Information
The Aeronautical Journal , Volume 91 , Issue 907 , September 1987 , pp. 333 - 337
Copyright
Copyright © Royal Aeronautical Society 1987 

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