The parallel Navier-Stokes code NSMB has been set up to allow an accurate computation of the flow field around a twin-engine aircraft configuration. A cost effective time integration method is used in conjunction with a genuine multidomain implementation of both algebraic and 1/2-equation turbulence models. The validation of the approach is presented, dealing with 2D and 3D test cases relevant to the general application of engine/airframe integration. An accurate prediction of the separation of the boundary layer induced by a pressure gradient is obtained by an enhanced Johnson-King type turbulence model. It is also shown the computed flow about a transonic wing-body configuration is quite sensitive to the turbulence model in use. The successful application of the code to the twin-engine aircraft AS28G configuration is presented with an emphasis on the sensitivity to the mesh size ranging from 04 to 3.5 millions points.
Application of Navier-Stokes methods for engine/airframe integration
Anwendung von Navier-Stokes-Methoden auf die Flugtriebwerk/Flugwerk-Integration
1996
12 Seiten, 6 Bilder, 17 Quellen
Conference paper
English
Application of Navier-Stokes Methods for Engine/Airframe Integration
British Library Conference Proceedings | 1996
|Navier-Stokes Analysis for Engine Airframe Integration
British Library Conference Proceedings | 1996
|Navier-Stokes Analysis for Engine Airframe Integration
British Library Online Contents | 1996
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