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Numerical solution of Euler equations foraerofoils in arbitrary unsteadymotion

Published online by Cambridge University Press:  04 July 2016

C. Q. Lin  and
K. Pahlke
C. Q. Lin
Affiliation:
Northwestern Polytechnical University Xi'an, China
K. Pahlke
Affiliation:
Institute for Design Aerodynamics, DLR Braunschweig, Germany
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Abstract

This paper is part of a DLR research programme todevelop a three-dimensional Euler code for thecalculation of unsteady flow fields aroundhelicopter rotors in forward flight. The presentresearch provides a code for the solution of Eulerequations around aerofoils in arbitrary unsteadymotion. The aerofoil is considered rigid in motion,and an O-grid system fixed to the moving aerofoil isgenerated once for all flow cases. Jameson's finitevolume method using Runge-Kutta time steppingschemes to solve Euler equations for steady flow isextended to unsteady flow. The essential steps ofthis paper are the determination of inviscidgoverning equations in integral form for the controlvolume varying with time in general, and itsapplication to the case in which the control volumeis rigid with motion. The implementation of animplicit residual averaging with variablecoefficients allows the CFL number to be increasedto about 60. The general description of the code,which includes the discussions of grid system, gridfineness, farfield distance, artificial dissipation,and CFL number, is given. Code validation isinvestigated by comparing results with those ofother numerical methods, as well as withexperimental results of an Onera two-bladed rotor innon-lifting flight. Some numerical examples otherthan periodic motion, such as angle-of-attackvariation, Mach number variation, and development ofpitching oscillation from steady state, are given inthis paper.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 976 , July 1994 , pp. 207 - 214
Copyright
Copyright © Royal Aeronautical Society 1994 

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References

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