Inviscid Computation of Effect of Wake Vortices on a Scale-Model Airplane
Struijs, R. and Jonville, G. and Darracq, D. and Heinrich, R. (2003) Inviscid Computation of Effect of Wake Vortices on a Scale-Model Airplane. AIAA Journal, 40 (1), pp. 100-109.
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Within the EU-project WAVENC the block structured DLR-FLOWer code has been applied to the inviscid simulation of a wake vortex encounter of a generic aircraft. The incoming vortices of the preceding aircraft are prescribed at the inflow boundary of the computational domain. This allows to capture a mutual interaction between aircraft and incoming vortices. In order to transport the vortices without too big numerical losses from the inflow boundary to the aircraft, very fine Cartesian grids, so-called "vortex transport meshes", have been embedded into the grid structure. This is enabled by the Chimera technique implemented in the code. One main advantage of this strategy is, that no remeshing is needed to perform a parametric study of the aircrafts position relative to the incoming vortices. Global forces and moments as well as pressure distributions obtained for different positions of the aircraft in the vortex disturbed flowfield show a good agreement to experimental data.
|Title:||Inviscid Computation of Effect of Wake Vortices on a Scale-Model Airplane|
|Journal or Publication Title:||AIAA Journal|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 100-109|
|Keywords:||Euler, wake vortex, steady flows, chimera|
|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|
|Location:||Köln-Porz , Braunschweig , Göttingen|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology|
|Deposited By:||Claudia Grant|
|Deposited On:||31 Jan 2006|
|Last Modified:||14 Jan 2010 19:24|
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