Numerical investigation aerodynamics nacelle-strake effect

The focus of this investigation is on the numerical prediction of the nacelle-strake effect on the lift coefficient for transport aircraft in high-lift configurations, i.e. the configurations used in the EUROLIFT II project. Within this project high-Reynolds-number wind-tunnel tests were conducted in the European Transonic Windtunnel (ETW) from 2004 to 2007. The geometry considered, also considered in the present investigation, was a commercial wide-body twin-jet high-lift configuration with flaps and slats in landing configuration. The wind-tunnel model considered is a wing/fuselage configuration with a high bypass ratio through-flow-nacelle with a core body. The complexity of the wind-tunnel model was increased in three successive stages. The final stage III geometry features a nacelle strake on the nacelle inboard surface to optimize the performance of the high-lift configuration. The applied CFD methods include the usage of hexahedral elements in regions of vortical flow, a RSM-g turbulence model and a version of the dissipation model in terms of Scalar and Matrix dissipation with various coefficients. Analysis of the results of the performed computations show that for the present configuration, the nacelle strake effect on maximum lift coefficient can be captured with high accuracy by using steady-flow computations and the CFD practices outlined in this paper.