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Vortex generators are most often used to delay flow separation.To accomplish this they are often placed on the external surfaces of vehicles [4] and wind turbine blades. On both aircraft and wind turbine blades they are usually installed quite close to the leading edge of the aerofoil in order to maintain steady airflow over the control surfaces at the trailing edge. [3]
When the speed is reduced and the aircraft approaches stall, the local flow at the leading edge is diverted outwards; this spanwise component of velocity around the vortilon creates a vortex streamed around the top surface, which energises the boundary layer. [6] A more turbulent boundary layer, in turn, delays the local flow separation.
Wingtip vortices can pose a hazard to aircraft, especially during the landing and takeoff phases of flight. The intensity or strength of the vortex is a function of aircraft size, speed, and configuration (flap setting, etc.).
Nose, wing and ventral strakes Vortices over the wing strakes of an F/A-18E Super Hornet. In aviation, a strake is an aerodynamic surface generally mounted on the fuselage of an aircraft to improve the flight characteristics either by controlling the airflow (acting as large vortex generators) or by a simple stabilising effect.
The Symphony SA-160 side view The Symphony SA-160 standard instrument panel Symphony SA-160 showing 40 degree deflection on its Fowler flaps and its aileron end fences The Symphony SA-160 has two unique vortex generators on its wing to ensure aileron effectiveness through the stall The OMF-100-135 Symphony Thielert Centurion 1.7 diesel equipped prototype
The aircraft crashed in July 1958 during a routine test flight. [185] Vulcan B.1 XA894 flew with five Olympus engines, the standard four Mk.101s, plus a reheated Olympus 320 destined for the BAC TSR-2 in an underslung nacelle. This aircraft was destroyed in a ground fire at Filton on 3 December 1962. [183]
On aircraft with swept wings, wing tip stall also produces an undesirable nose-up pitching moment which hampers recovery from the stall. Washout may be accomplished by other means e.g. modified aerofoil section, vortex generators, leading edge wing fences, notches, or stall strips. This is referred to as aerodynamic washout.
Wings which generate vortex lift have been used on delta-winged research aircraft such as the Convair XF-92A and Fairey Delta 2. Early delta wing fighters such as the F-102 , the F-106 , and contemporaries such as Dassault's deltas had cambered leading edges that were blunt and did not generate significant vortexes.
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