Essay About Freestream Cases        Results        Freestream Cases And Ground Effect Cases        Boundary Conditions

Race Car Aerodynamics Turbulence
SESA6039 Race Car Aerodynamics Laboratory Exercise 2AbstractThe flow past a front wing element is simulated two-dimensionally in FLUENT. The variation of aerodynamic forces with height and angle of attack were observed. The resultant increase in aerodynamic efficiency with decrease in ride height and decrease in efficiency with increasing angles of attack is quantified and explained with the aid of contour plots obtained for static pressure and velocity. The key role of y+ and courant number in computational fluid dynamics problems is also explained.Table of ContentsAbstract        Nomenclature        Introduction        Method        Numerical Model        Grid Meshing        Boundary Conditions        Boundary conditions for ground effect cases        Boundary conditions for freestream cases        Results        Freestream cases                [pic 1]        [pic 2]        [pic 3]Wing in ground effect        h/c = 0.25        h/c = 1        Unsteady flow at         [pic 4]Courant number        Conclusion        References        List of Figures and Tables        NomenclatureWIG – Wing in groundRe – Reynolds number U∞ – Freestream velocityRANS – Reynolds Averaged Navier StokesAoA – Angle of attackc – Aerofoil chord  h – Distance from the moving ground RMS – Root mean squaredCL – Coefficient of liftCD – Coefficient of dragP – Pressurev – VelocityCFD – Computational Fluid DynamicsIntroductionThe flow past a Tyrell 098 main front wing element was simulated using the CFD program FLUENT. The wing element was placed in freestream at three different angles of attack (AoA) and two cases in close proximity to the moving ground. A low speed flow passing a downforce generating wing both in and out of ground effect was modelled.  Several physical features were investigated including downforce and drag and its variation with height and angle of attack. Unsteady freestream simulations were also examined at higher angles of attack. The aerofoil was modelled in 2D to allow for swift grid generation, easy specification of the boundary conditions and significantly shorter solution times.