A multipoint inverse method for multi-element airfoil design

Ashok Gopalarathnam, Michael S. Selig

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A multipoint inverse method for the design of multi-element airfoils is presented. The method uses an isolated-airfoil, multipoint, inverse code to generate each element of the multi-element airfoil and a two dimensional panel method is used to analyze the multi-element airfoil. The isolated airfoil inviscid velocity distributions are used as design variables to achieve prescribed inviscid velocity distributions for the multi-element airfoil. Each element is divided into segments. The isolated airfoil velocity distribution over each segment at a specified lift coefficient is adjusted to achieve the desired velocity distribution over the corresponding segment of the multielement airfoil at the specified operating condition. This procedure is automated using an efficient multidimensional Newton iteration. The method thus allows for rapid, interactive design of a multi-element airfoil with a desired inviscid behavior, which can then be analyzed using more computationally demanding viscous codes.

Original languageEnglish (US)
Title of host publication14th Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages197-205
Number of pages9
ISBN (Print)9781563472121
DOIs
StatePublished - 1996
Event14th Applied Aerodynamics Conference, 1996 - New Orleans, United States
Duration: Jun 17 1996Jun 20 1996

Publication series

Name14th Applied Aerodynamics Conference

Other

Other14th Applied Aerodynamics Conference, 1996
CountryUnited States
CityNew Orleans
Period6/17/966/20/96

ASJC Scopus subject areas

  • Engineering(all)

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  • Cite this

    Gopalarathnam, A., & Selig, M. S. (1996). A multipoint inverse method for multi-element airfoil design. In 14th Applied Aerodynamics Conference (pp. 197-205). [AIAA-96-2396] (14th Applied Aerodynamics Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.1996-2396