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Inviscid and viscous simulations of spoiler performance

Published online by Cambridge University Press:  04 July 2016

C. Xu ,
W. W. H. Yeung  and
R. W. Guo
C. Xu
Affiliation:
Department of Mechanical EngineeringUniversity of Wisconsin, Milwaukee, USA
W. W. H. Yeung
Affiliation:
School of Mechanical and Production EngineeringNanyang Technological University, Singapore
R. W. Guo
Affiliation:
Department of Power EngineeringNanjing University of Aeronautics and Astronautics, China
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Abstract

Inviscid and viscous computational models have been used to predict two-dimensional steady separated flow around an aerofoil with a spoiler. First, an attempt is made to construct an inviscid panel method in which piece-wise linear vortex panels are placed on the aerofoil and spoiler. The separated region is modelled with potential flow analysis by using free vortex sheets placed on the separation streamline from the spoiler tip and aerofoil trailing-edge. The shapes of the vortex sheets require an iteration to be established. The calculation is based on an assumption of the length of the free vortex sheets. Second, a viscous procedure based on a finite control volume scheme is used to solve the Navier-Stokes equations for turbulent flow by making used of the k-ε model. An algebraic pressure correction is incorporated in the calculation. The predictions from the two models are in reasonable agreement with experimental measurements.

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1017 , September 1998 , pp. 399 - 405
Copyright
Copyright © Royal Aeronautical Society 1998 

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