Advances in Simulation of Wing and Nacelle Stall (eBook)

The Delay of RANS-to-LES Transition in Hybrid RANS-LES Approaches and Some Recently Proposed Remedies.- Computations of Separated Flows with a Hybrid RANS/LES Approach.- Hybrid RANS/LES Study of the Development ofan Airfoil-Generated Vortex.- Interaction of Three-Dimensional Disturbances with the Flow around a Two-Element High-LiftAirfoil.- The Discontinuous Galerkin Method as anEnabling Technology for DNS and LES of Industrial Aeronautical Applications.- Body Force Modelling of Internal Geometry forJet Noise Prediction.- Numerical Studies of Turbulent Flow Influenceon a Two-Element Airfoil.- CFD for Prediction of Flow Separation from Aircraft Tail Surfaces.- Zonal RANS-LES Computation forNear-Stall-Airfoil Flow.- Criteria for Crosswind Variations duringApproach and Touchdown at Airports.- Development and Improvement of Two Methods of Different Complexity to SimulateAtmospheric Boundary Layer Turbulence for Aircraft Design Studies.- Simulation of Interaction of Aircraft with Gust and ResolvedLES-Simulated Atmospheric Turbulence.- A New Method to Generate Anisotropic Synthetic Turbulence for LES.- Numerical Simulation of the Turbulent Flow Around a Wing.- Integration- and Intake-Induced Flow Distortions and their Impact on Aerodynamic Fan Performance.- Flow Investigations in a Stalling Nacelle Inlet Under Disturbed Inflow.- Realistic Inlet Distortion Patterns Interacting with a Transonic Compressor Stage.- Unsteady CFD Simulation of Transonic Axial Compressor Stages with Distorted Inflow.- Transitional Shock-Wave/Boundary-Layer Interactions in Intakes at Incidence.-Advanced Design Approach for a High-lift Wind Tunnel Model Based on Flight Test Data.- Simulation of Longitudinal Vortices on a High-LiftWing.- Impact of Different UHBR-Engine Positions on the Aerodynamics of a High-LiftWing.- Numerical Investigation of the Influence of Pressure Belts on the Stall of a Transport Aircraft in Landing Configuration.- Numerical Studies of Active Flow Control Applied at the Engine-Wing Junction.