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de aerodynamische kant van een vliegtuig vleugel

CFD simulation of straight wing. Span:10m, chord:1m.

This project  involves meshing externally an F1 type Front Wing, and then simulating its' operation when facing a horizontal airflow of 20 m/s. Nowadays it is very common to witness F1 type cars using this type of leaf-like wings, called cascades, acting to generate vortices behind them that spiral upwards and outwards in channels controlled to the millimeter and shaped around the front wheels, towards the underfloor, through and around radiator inlets and between suspension components, and lately , it has been introduced by some Formula Student teams as well.  For this case a Symmetry plane was added midst the Part, and half the part was used for meshing and simulation for simplification. A steady state incompressible flow simulation is executed to visualize the air flow around the bodywork and wings of the part, as well as the pressure distribution, the outwash effect of the cascade and endplate, as well as the vortices of the footplate.

Testing the frontwing of the civic type r

Test of wing section on a NACA 2412 airfoil

This  Study, investigates the possibility and the benefits of using a cross-flow fan embedded in an airfoil for simultaneous circulation control and thrust generation. In the propulsive wing concept, a cross flow fan is placed near the trailing edge of an airfoil section. When the fan starts to operate, the flow is drawn from the suction surface, provided by energy through the cross-flow fan and expelled out of the airfoil trailing edge

To find the drag and lift forces of the wing

CFD simulation is used to analyse the drag and lift of a front wing of a Formula Student Car. The main goal is to find the optimum angle of the flap for highest aerodynamic efficieny

An experiment to visually demonstrate the difference in lift generation between delta and straight wings, and why the delta wing has a more steady stall.

CFD analysis to verify the experimental results carried out on NACA 64015A Swpetback wing at AoA zero degree and Sweep angle 20 degrees.

Reference:  http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980227185.pdf

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