# Aerodynamic Computations Using a Finite Volume Method with an HLLC Numerical Flux Function

L. Remaki; O. Hassan; K. Morgan

Mathematical Modelling of Natural Phenomena (2011)

- Volume: 6, Issue: 3, page 189-212
- ISSN: 0973-5348

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topRemaki, L., Hassan, O., and Morgan, K.. "Aerodynamic Computations Using a Finite Volume Method with an HLLC Numerical Flux Function." Mathematical Modelling of Natural Phenomena 6.3 (2011): 189-212. <http://eudml.org/doc/222299>.

@article{Remaki2011,

abstract = {A finite volume method for the simulation of compressible aerodynamic flows is described.
Stabilisation and shock capturing is achieved by the use of an HLLC consistent numerical
flux function, with acoustic wave improvement. The method is implemented on an
unstructured hybrid mesh in three dimensions. A solution of higher order accuracy is
obtained by reconstruction, using an iteratively corrected least squares process, and by a
new limiting procedure. The numerical performance of the complete approach is demonstrated
by considering its application to the simulation of steady turbulent transonic flow over
an ONERA M6 wing and to a steady inviscid supersonic flow over a modern military aircraft
configuration.},

author = {Remaki, L., Hassan, O., Morgan, K.},

journal = {Mathematical Modelling of Natural Phenomena},

keywords = {aerodynamic flows; finite volume method; HLLC flux function; solution reconstruction; slope limiting},

language = {eng},

month = {5},

number = {3},

pages = {189-212},

publisher = {EDP Sciences},

title = {Aerodynamic Computations Using a Finite Volume Method with an HLLC Numerical Flux Function},

url = {http://eudml.org/doc/222299},

volume = {6},

year = {2011},

}

TY - JOUR

AU - Remaki, L.

AU - Hassan, O.

AU - Morgan, K.

TI - Aerodynamic Computations Using a Finite Volume Method with an HLLC Numerical Flux Function

JO - Mathematical Modelling of Natural Phenomena

DA - 2011/5//

PB - EDP Sciences

VL - 6

IS - 3

SP - 189

EP - 212

AB - A finite volume method for the simulation of compressible aerodynamic flows is described.
Stabilisation and shock capturing is achieved by the use of an HLLC consistent numerical
flux function, with acoustic wave improvement. The method is implemented on an
unstructured hybrid mesh in three dimensions. A solution of higher order accuracy is
obtained by reconstruction, using an iteratively corrected least squares process, and by a
new limiting procedure. The numerical performance of the complete approach is demonstrated
by considering its application to the simulation of steady turbulent transonic flow over
an ONERA M6 wing and to a steady inviscid supersonic flow over a modern military aircraft
configuration.

LA - eng

KW - aerodynamic flows; finite volume method; HLLC flux function; solution reconstruction; slope limiting

UR - http://eudml.org/doc/222299

ER -

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