Transonic Flow Past Conically Cambered Wings

Autores/as

Palabras clave:

conical camber, panel mehods, cfd, pressure distribution

Resumen

The flow is analysed over conically cambered wings for transonic flow conditions. Wing Planform is conically cambered for supersonic flow for minimum induced drag.  The circulation to determine the forces is developed using panel methods. Objective function for drag minima is formed using Lagrange multipliers. The transonic flow computations are  progressed through computational fluid dynamics. In case of a subsonic leading edge in supersonic flow there is no shock wave that appears over the wing, whether the wing is non-optimal or optimally cambered. This is advantageous towards optimization. The tip region is seen to have appreciable difference 

Biografía del autor/a

  • Prof. S.C. Gupta, MVJ College of Engineering
    Professor & HeadDepartment of Aeronautical Engineering

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Archivos adicionales

Publicado

2013-04-10

Número

Vol. 3 Núm. 1 (2013)

Sección

Research Articles

Licencia

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