A hybrid method for multipoint inverse wing design

Ashok Gopalarathnam, Michael S Selig

Research output: Contribution to conferencePaper

Abstract

A multipoint inverse method has been developed for wing design in incompressible flow. The method allows the designer to prescribe inviscid velocity distributions over different cross sections of the wing in a multipoint fashion. In addition to the velocity prescriptions, geometric parameters such as airfoil thickness and camber can be specified for the cross-section shapes. The design method uses a hybrid approach to determine the shapes of the wing cross sections that satisfy these design specifications. The airfoils forming the cross sections of the wing are generated using an inverse code for isolated airfoil design. A three-dimensional panel method is then used to obtain the inviscid velocity distributions over the resulting wing. The isolated airfoil velocity distributions are then used as design variables in a multidimensional Newton iteration method to achieve the design specifications on the wing. A key feature of the design method is a scheme to avoid using the panel method for sensitivity computations for the Newton iterations. As demonstrated in the paper, this scheme results in significant reductions in computation time as well as enables the use of a "canned" three-dimensional analysis method. Examples are shown to demonstrate the usefulness of the method.

Original languageEnglish (US)
StatePublished - Jan 1 1999
Event37th Aerospace Sciences Meeting and Exhibit, 1999 - Reno, United States
Duration: Jan 11 1999Jan 14 1999

Other

Other37th Aerospace Sciences Meeting and Exhibit, 1999
CountryUnited States
CityReno
Period1/11/991/14/99

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ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Gopalarathnam, A., & Selig, M. S. (1999). A hybrid method for multipoint inverse wing design. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.