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Two-dimensional implicit flux split steady and unsteady Euler calculations using unstructured moving grids

Published online by Cambridge University Press:  04 July 2016

K. P. Sinhamahapatra  and
N. Singh
K. P. Sinhamahapatra
Affiliation:
Aerospace Engineering Department, Indian Institute of Technology, Kharagpur, India
N. Singh
Affiliation:
Aerospace Engineering Department, Indian Institute of Technology, Kharagpur, India
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Abstract

Two-dimensional Euler equations are solved on unstructured triangular meshes using commonly available minicomputers. The driving algorithm is an upwind biased implicit cell-centred finite volume scheme. The spatial discretisation involves a naturally dissipative flux-split approach that sharply captures Shockwaves. The grid generation method uses a type of advancing front technique which triangulates a given set of points. To demonstrate the application, the steady flow results are presented for single and two component aerofoils. The unsteady results are obtained using a dynamic mesh algorithm for an aerofoil pitching harmonically about the quarter chord. The paper presents a description of the grid generation and movement algorithm and of the Euler solver, along with results and comparison that assess their capabilities.

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1003 , March 1997 , pp. 131 - 139
Copyright
Copyright © Royal Aeronautical Society 1997 

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