Computation of the Helicopter Fuselage Wake with the SST, SAS, DES and XLES Models
Le Chuiton, Frederic and D'Alascio, A. and Barakos, G. and Steijl, R. and Schwamborn, Dieter and Lüdeke, Heinrich (2008) Computation of the Helicopter Fuselage Wake with the SST, SAS, DES and XLES Models. In: Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) Advances in Hybrid RANS-LES Modelling, Vol.: 97. Springer-Verlag Berlin. ISBN 978-3-540-77813-4.
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Abstract This paper presents a first industrial attempt at Eurocopter Germany to use DESlike methods to compute the wake behind a helicopter in forward flight. Three codes have been used: TAU (DLR), CFX (Ansys) and HMB (Uni. Liverpool) and four different turbulence models: standard SST and three of its unsteady extensions SAS, DES and XLES. Results for the loads, pressure distribution and skin-friction lines have been compared to each other and against wind tunnel experimental data. These more sophisticated models brought improvements over the base SST but not always markedly and consistently: the drag gets improved although the negative lift on the body departs further form the experimental value. The pressure distribution on the backdoor has been improved by one of the computation. Oil-flow visualisation results show that the mean flow in the region of the backdoor is qualitatively reasonably well captured.
|Document Type:||Book Section|
|Title:||Computation of the Helicopter Fuselage Wake with the SST, SAS, DES and XLES Models|
|Journal or Publication Title:||Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM)|
|In ISI Web of Science:||No|
|Series Name:||Advances in Hybrid RANS-LES Modelling|
|Keywords:||DES, TAU, CFX, HMB, DLR, computation, Helicopter Fuselage Wake, Models|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L AR - Aircraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L AR - Aircraft Research|
|DLR - Research theme (Project):||L - Concepts & Integration|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > CASE|
|Deposited By:||Ulrike Schubert|
|Deposited On:||08 Jan 2009|
|Last Modified:||27 Apr 2009 14:42|
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