Aerodynamic Design of High-Lift Devices for Civil Transport Aircraft Using RANS CFD

Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

“…Aircraft wing high-lift configuration design is an important and challenging part of the whole aircraft aerodynamic configuration design, even dealing with a 2D high-lift configuration design task which is an essential step for the 3D high-lift configuration design [1], [2], [3], [4].…”

“…The computations normally include a comprehensive code, coupled to Euler or Navier-Stockes solvers. The examples for a successful application of CFD are the codes FLUENT, OVERFLOW of NASA, FLOWer and TAU of Deutshes Zentrum für Luft und Raumfahr [4], [6], elsA and WAVES of ONERA [7], CFD++ [8], Star-CCM+ [9], [10], TAS of Takoku University and UPACS of Japan Institute of Space Technology and Aeronautics [11,12].…”

“…A hybrid mesh contains of a mixture of structured portions and unstructured portions. It integrates the structured meshes and the unstructured meshes in an efficient manner, [4].…”

Flow Structure Past a Canonical Shape of Engine/Pylon/Wing Installation for Takeoff/Landing Conditions

“…Such designs, hereafter denoted as close coupled, promote a stronger and more complex aerodynamic interaction between the engine nacelle and the wing, both for cruise flight conditions, in which unsteady interference may affect the aeroelastic stability of the aircraft [14], but also during the takeoff and landing phases, in which the aircraft is operating at a moderate, or even a relatively high, angle of attack. During these particular flight phases, the power-plant-to-wing proximity promotes the occurrence of a complex vortex dynamics at the junction between the nacelle, the pylon, and the wing, which is advected along the upper wing [15]. The interaction of these vortices with the boundary layer on the suction side of the wing can lead to local flow separation [15][16][17], responsible for a drop in aircraft aerodynamic performances [18,19] and a potential premature stall mechanism [20].…”

“…During these particular flight phases, the power-plant-to-wing proximity promotes the occurrence of a complex vortex dynamics at the junction between the nacelle, the pylon, and the wing, which is advected along the upper wing [15]. The interaction of these vortices with the boundary layer on the suction side of the wing can lead to local flow separation [15][16][17], responsible for a drop in aircraft aerodynamic performances [18,19] and a potential premature stall mechanism [20].…”