The invention is related to airfoils of wind turbines, planes or helicopters, meant for the generation of aerodynamic lift.

Both wind turbines, planes and helicopters are using airfoils which need to have a high lift coefficient and good lift/drag performance. It is state of the art to apply vortex generators to existing airfoils since it is known that this will increase the maximum lift coefficient. However even after much research efforts, the use of vortex generators has not shown a breakthrough development since it is associated with the following problems.

The performance of an airfoil can be expressed by the lift coefficient and the lift over drag ratio. The precise required values depend on the technical application of the airfoil, however in general, when the application of vortex generators is considered, the designer has an airfoil without vortex generators which performs well up to a certain angle of attack (ONVG), and wants to extend the good performance range beyond QNVG by using vortex generators. This can be realized with classical vortex generators however for angle of attack below a _N vG _> the lift over drag ratio decreases substantially. This is usually not acceptable. For example in WO90/11929 by Wheeler a large number of geometries is proposed. This publication does not disclose which geometry would give acceptable performance. It was shown that the geometries revealed by Wheeler in figures 1 and 2 and 4 did not provide airfoil performance which was better than that of airfoils without vortex generators. Also WO00/15961 discloses several geometries which are shown not to give acceptable performance.

A second though problem is that the attachment of vortex generators often fails. Vortex generators usually exist of baseplates with one or more fins which are glued on the airfoil surface. In the practice of wind turbines the vortex generators come loose within weeks or a few years. It was tried to increase the size of the base so that the attachment area was increased. This idea did not give better fixation. For example in EP 2031243A1 by LM a radical solution was proposed by submerging vortex generators in the airfoil surface. However it should be noted that airfoil have to pass through high bending moments, which means that the surface experiences high stress and thus that a discontinuity in the surface such as is proposed by LM is unacceptable. Another attempt was to produce strips with multiple vortex generator pairs so that many vg-fins could be applied quickly and the full strip surface was fixed by adhesive. Strips of plastic and of aluminium have been applied on many rotor blades but came loose within a few weeks - years. Also the fixation of the strips with high quality silicone based adhesive did not improve the situation.

A third problem is that the vortex generator should be resistant to all possible weather conditions, which also sets shape demands. For example a thickness of 2-5 mm or more in particular 3-4mm is required for standard plastics to have long term UV-resistance. Such thickness cause the vortex generator to become stiff so that it cannot adapt to the shape of the airfoil surface. Furthermore such thickness for the baseplate of the vortex generator means that the flow has to step up and step down the baseplate over at least the 2-5 mm and it means that the vortex generator fins need to be relatively thick which all leads to poor aerodynamic performance. Another attempt to solve this problem was to place the vg-strips in a recess in the blade surface. The aim was to reduce the aerodynamic drag caused by the strips when place on top of the surface. In practice however it was not feasible to produce the recess and the vg-strips so accurately that, the blade surface was smooth with the vg-strips positioned in the recess. Furthermore also these vgs did come loose quickly and the recess in the blade surface reduced building height and caused cracks in the surface.

A fourth problem is that the vortex generator should be easily applicable and should be shaped such that objects would not become stuck by the vortex generator fins and should not be intrusive in the airfoil. In the practice of wind energy often triangular shaped vortex generator fins are applied since this shape is proven to generate strong vortices, however the sharp edges could injure service personel and do obstruct hoisting belts. It is clear that this problem also sets demands on the shape so that it becomes even more difficult to obtain an aerodynamically optimized shape. It is known from fundamental theoretical analysis and not doubted that strong vortices are generated when a bound aerodynamic circulation suddenly stops. This is why the sharp edge triangular form and also a sharp edges rectangular form cannot be avoided when strong concentrated vortices are required. So expert in the art has not much room to solve the problems.

In the light of the above problems it needs explanation why vortex generators are often applied to stall regulated wind turbines. The reason is that many stall regulated turbines suffered from large underperformance and that the applcation of vortex generators could solve this to a large extent. However the solution was not durable since the vortex generators came loose. Therefore designers of wind turbines put effort in new blade and airfoil designs which didn't require vortex generators. This design method was rather succesful and therefore state of the art wind turbines usually no longer have vortex generators.

The aim of the invention is to overcome the above mentioned disadvantages.

The invention is an airfoil of chord c with a thickness of more than 20%c and in particular of more than 25%c comprising a vortex generator pair between chordwise position 20%c and 70%c, said vortex generator pair comprising 2 not directly connected fins and a base which interconnects said fins and where said fins are placed under opposite angles of attack, characterized in that said fins are cambered by at least 1% in particular by at least 2% and more particularly by a least 3% of the fin chord. The camber of the fins resulted in better aerodynamic performance and gave stiffness to the fins at the same time. The fins could be made very thin without becoming to flexible due to the camber. And thinner fins require less material. Furthermore thanks to the camber of the fins, the baseplate becomes flexible and can follow a range of curvatures of the airfoil surface where the vortex generator pair is attached. In case of uncambered fins the baseplate becomes very stiff and has only one fixed curvature. Conclusively the camber of the fins also improves the attachement of the vortex generator pair to the surface. Amazingly the addition of camber in the fins lead to 4 advantages: better aerodynamics, better fixation, high stiffness of the fins and low material use.

According to an embodiment of the above invention the airfoil is suitabel for planes and helicopters even for airfoils of less than 20%c thickness when the vortex generator pair is attached between 20%c and 50%c. A break trough thought was that the classical idea that a vortex generator should generate concentrated strong vortices turned out to be incorrect. Instead it was found that non-concentrated vorticity is even more effective and thus that fins which have a rounded trailing edge lead to better airfoil performance. According to the inventor the vortex generator is effective by mixing high speed air from outside the boundary layer with low speed air inside the boundary layer (this is known) and by transporting low speed air from inside the boundary layer to outside the boundary layer (this is new). This second effects is stronger when vorticity is not concentrated but distributed and when vortex generator pairs are applied of which the fins generate opposite vorticity.

Therefore, according to an embodiment of the invention the lateral area of the trailing half of the fins of the vortex generator is less than 45% and in particular less than 40% of the product of the fin chord and the fin height. An amazing conclusion was that the thought that the fixation problem of the vgs could be solved by enlarging the base was wrong and that instead the fixation improved by reducing the base plate and chosing a shape which allows thermal expansion.

Therefore a beneficial embodiment of the invention is that wherein the base shaped like a 'U', a V or a W and that wherein the base is essentially not extending beyond the area between the fins. At the same time those shapes lead to better aerodynamic performance. More benefit is obtained when the base comprises 2 subfins which are smaller than the main fins and which are located in between said main fins. The height of the subfins is typically between 5% and 30% of that of the main fins.

More benefit is obtained when the distance measured half way the fin chord between the suction sides of adjacent main fins of different vortex generator pairs is at least 120% and preferably about 150% of the distance between pressure sides of adjacent main fins of a vortex generator pair.

According to a beneficial embodiment of the invention the largest length in lateral direction in solid base material is less than 100% in particular less than 90% and more in particular less than 70% of the bottom fin chord.

According to another beneficial embodiment of the invention the edge length of the base has an angle with the design inflow direction between 50 and 0 degrees over more than 70%, in particular more than 80%, and more in particular 90% of its length.

According to another beneficial embodiment of the invention the base is fixed to the airfoil surface by double sided adhesive tape with a thickness of at least 0.3%, for example at least 0.5% and for example about 1% of the largest length in solid baseplate material.

According to another beneficial embodiment of the invention the vortex generator pair and the airfoil surface form a solid body without voids or air inclusions.

According to another beneficial embodiment of the invention the height of the main fins is between 2%c and 6%c.

According to another beneficial embodiment of the invention the airfoil thickness can be less than 20%c thickness in case it should be robust for surface contamination.

According to a further beneficial embodiment of the invention the airfoil comprises a vortex generator pair and 2 fins, characterized in that the lateral area of the trailing 50% of said fins is less than 200% and preferably less than 50% of the lateral area of the leading 50% of said fins. A car roof top container should have a shape which provides a large volume, which has the drawback that the container adds much aerodynamic drag to a car and therefore increases fuel consumption. This problem can be solved by the application of vortex generators to the container according to any of the following embodiments.

1. Car roof top container characterized in that it comprises vortex generators and that its lateral cross section at 95% length is less than 60% of its maximum lateral cross section.

2. Car roof top container according to claim 1 characterized in that the lateral cross section at 95% length is less than 50%, in particular less than 40% and more in particular less than 30% of the maximum lateral cross section.

3. Car roof top container according to claim 1 or 2 characterized in that the vortex

generators are located in the length range between 40%L and 90%L.

4. Car roof top container according to claim 1 or 2 characterized in that the vortex

generators are located near the length position of maximum lateral cross section or not further than 10% length forward of not further than 20% length position backward.

5. Car roof top container according to any of the preceding claims comprising vortex generators which are attached as separate elements or are integrated with said container.

6. Car roof top container according to any of the preceding claims compricing vortex generators which are at or below the maximum height of said container.

7. Car roof top container optionally according to any of the preceding claims comprising flow guidance elements for the supports.

8. Car roof top container according to claim 7 comprising flow guidance elements.

9. Car roof top container according to any of the preceding claims wherein the angle of the surface of the rear end is more than 20 degrees and in particular more than 25 degrees over at least 20%L. In order to explain the invention further some definitions are introduced.

Camber, camber can refer to an airfoil section of the blade or to a fin of a vortex generator (vg). In the first case it is the maximum distance between the chord line of the airfoil and the camber line in per cent of the chord. In the case of the vg fin it analogously refers to the maximum distance between the camber line and the fin chord line, where both lines are taken at 30% of the fin height above the blade surface and wherein the fin height is the maximum height of the fin above the blade surface. Fin-chord: the chord of the fin of a vg at 10% of the fin height above the blade surface. The bottom-fin-chord is defined as the length over which the fin is connected to the base.

Edge-length of base: the total length of the contour of the projection of the base on the blade surface.

Distance between fins: the distance between fins refers to the distance between the highest fins or the main fins of a vortex generator pair.

Other embodiments according to the invention are the following:

That wherein the vortex generator exists of a separate base and separate fins which can be connected by a click-joint. For example for the transportation of wind turbine blades it is beneficial when the fins can be installed after the blades are at the site.

That wherein the fin of a vortex generator pair has a trailing part which is loose from the base so that is flexes by the flow: at high flow speeds this part could be aligned with the flow while at low flow speeds it is inclined with the flow by e.g. 10 degrees so that strong vortices are created. Also the incilination to the flow can be a function of temperature by using a bi-metal. This could be beneficial to delay stall at high temepartures and advance it at lower temperatures to compensate for air temparture dependence of stall power levels of stall controlled wind turbines.

That wherein the fins of vortex generator pairs are controlled automatically for example by magnetic actuators below the airfoil surface which control the position or orientation of the fins.

That wherein the cross section of a fin has a J-shape, where the lower part of the J is connected to the airfoil surface and the vertical part of the J is the protruding fin, so that the fin can be pushed against the airfoil surface by taking away the curvature of the J. That wherein the fins of a vortex generator pair are essentially aligned with tangentials about the rotor axis, so that the angle of attack of the fins is close to zero in case of 2D- flow but increases with an increasing radial component in the flow which means that the angle of attack is low when the blade surface is clean and that the angle of attack increases with increasing surface contamination since the higher contamination leads a thicker boundary layer and thus to a larger radial component in the flow by the radial pressure gradient and the centrifugal force.

That wherein the vortex generator pair is applied to a wind turbine blade and the spacing between vortex generator pairs is larger than 10%c and in particular larger than 20%c and more in particular larger than 30%c, where the spacing is measured from the centre of a pair to the centre of an adjacent pair.

That wherein the vortex generator pair is made of a material essentially consisting of PVC or PVDF or aluminum. The fixation of the vortex generator pair to an airfoil of a plane can be done by welding, screws, pop-nails, double sided adhesive tape.

That wherein the vortex generator pair comprises a base of which the lower side is concave so that it fits well to the convex suction side of thae airfoil and in particular that the radius of curvature of the concave bottom side is less than the radius of curvature of the convex suction side.

That wherein the vortex generator base and double sided adhesive are joint with a primer under controlled conditions.

Figures

Figure 1 Lift coefficient improvement by vortex generator.

Figure 2 Lift/drag ratio improvement by vortex generator.

Figure 3 Airfoil with 3 vortex generator pairs.

Figure 4 Side view of a vortex generator pair.

Figure 5: Front view of a vortex generator pair.

Figure 6: Top view of a W-shaped vortex generator pair.

Figure 7: Top view of a U-shaped vortex generator pair.

Figure 8: Top view of a V-shaped vortex generator pair.

Figure 9: Car roof top container.

Figure 1 shows the lift coefficient q as a function of the angle of attack of a 40% thick airfoil. It can be seen that the lift coefficient for the case with vortex generators installed at 30%c (label VG30 cl) is (much) higher in the range from 0 to 26 degrees compared to the result without vortex generators (label NVG cl). Figure 2 shows the rato of lift over drag for the same configuration. It can be seen that L/D is (much) better for the angle of attack range between 2 and 22 degrees. The results are obtained by CFD-simulation. Figure 3 shows an airfoil 1 with chord 2 and three vortex generator pairs 3 which are installed on the airfoil surface 6. The vortex generator pairs are shown on a larger scale than the airfoil for illustrative reasons. Each vortex generator pair has two fins 5 and a base 4 which are only labelled for one vortex generator pair. The distance between the pressure sides of the fins of a vortex generator pair 8 is less than the distance between the suction sides of adjacent fins of different vortex generator pairs. Figure 4 shows a side view of a vortex generator pair which is fixed by double sided adhesive tape which has an adhesive layer 10 fixed to the base of the vortex generator pair and am adhesive layer 11 fixed to the airfoil surface 6 and in between a foam layer 12. The thickness of layer 10, 11 and 12 are shown thicker than realistic for illustrative reasons. Figure 5 shows a front view of a vortex generator pair. Figure 6 shows a top view of a W-shaped vortex generator pair and de design inflow direction 14. The lateral direction is defined as perpendicular to the design inflow direction and in the base of the vortex generator pair. Figure 7 shows a top view of a U-shaped vortex generator pair. Figure 8 shows a top view of a V-shaped vortex generator pair. Figure 9 shows a car roof top container 20, with a length L between the front end 21 and a rear end 22, whereon a vortex generator fin 23 is installed. The upper surface of the trailing part of the container 24 has an angle 25 with the horizontal.

Although the illustrative embodiments of the present invention have been described in greater detail with reference to the accompanying drawings, it will be understood that the invention is not limited to those embodiments. Various changes or modifications may be effected by one skilled in the art without departing from the scope or the spirit of the invention as defined in the claims. Furthermore the validity of the claims is not dependent on the correctness of physical explanations.

It is to be understood that in the present application, the term "comprising" does not exclude other elements or steps. Also, each of the terms "a" and "an" does not exclude a plurality. Any reference sign(s) in the claims shall not be construed as limiting the scope of the claims.