Abstract
Spoilers are widely used on aircrafts as lateral control devices. Despite their wide usage, very little numerical and theoretical information exist. Numerical simulation of the full unsteady, compressible Euler’s equations over the NACA 23012 airfoil with spoiler is performed using a hybrid Least-Squares finite element/finite difference method coupled to the Newton-Raphson’s linearization technique. The flow patterns behind the spoiler are presented. The pressure coefficient over the upper and lower surfaces are successfully compared to previously published experimental work. The vortex shedding due to the existence of the spoiler is strong specially at high deflection angles. Convection of the vortices will affect the performance of the tail and so a future study of the wing-tail interaction is needed.
Highlights
Spoilers are devices intended to reduce the lift force of an airfoil in a controlled manner
A numerical study using zonal detached eddy simulation (ZDES) is carried out by Gand [7] shows that the use of zonal detached eddy simulation (ZDES) significantly improves the prediction of the spoiler mean hinge moment compared to the computation performed with a standard Reynolds-averaged Navier– Stokes (RANS)/Spalart Allmaras model on the same grid
Wang and Liu [9] examined the influence of the downward spoiler deflection on the boundary layer flow of a high-lift two-element airfoil consisting of a droop nose, a main wing, a downward deflecting spoiler and a single slotted flap
Summary
Spoilers ( called lift dumpers) are devices intended to reduce the lift force of an airfoil in a controlled manner. The flow on the lower airfoil surface leaves the trailing edge and convects into wake. These shedding vortices make the wake highly turbulent and oscillatory. Alhawwary et al [8] simulated numerically the flow field around the BATR airfoil-spoiler configuration with deflected spoiler using the higher order spectral difference method by solving the compressible twodimensional, full Navier--Stokes equations on unstructured quadrilateral grids. Wang and Liu [9] examined the influence of the downward spoiler deflection on the boundary layer flow of a high-lift two-element airfoil consisting of a droop nose, a main wing, a downward deflecting spoiler and a single slotted flap.
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