| Issue |
Math. Model. Nat. Phenom.
Volume 6, Number 3, 2011
Computational aerodynamics
|
|
|---|---|---|
| Page(s) | 189 - 212 | |
| DOI | https://doi.org/10.1051/mmnp/20116308 | |
| Published online | 16 May 2011 | |
Aerodynamic Computations Using a Finite Volume Method with an HLLC Numerical Flux Function
School of Engineering, Swansea University,
Swansea SA2 8PP,
Wales,
UK
⋆ Corresponding author. E-mail:
l.remaki@swansea.ac.uk
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.
Mathematics Subject Classification: 65M08 / 65M50 / 76J20
Key words: aerodynamic flows / finite volume method / HLLC flux function / solution reconstruction / slope limiting
© EDP Sciences, 2011
Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.