Doug Lord
Flight Ready
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First Foiling America's Cup
Great stuff here-thanks Slavi!
==================Rule 5.14 is very badly written, imo. Anything one puts into a water flow will alter the velocity and pressure field around it, and will hence alter the boundary layer. In the same moment they have put the horizontal elevator to the rudder, it has modified the flow field around the hull and the rudder. So, the rule 5.14 is practically very hard to enforce in a literal sense.
However, if one wants to read it literally, any device on the surface of the airfoil or of the hull, the purpose of which is to modify the water flow (and hence the boundary layer) around the foil or the hull, is prohibited.
But... What if it is not ON the surface but IS the surface or an integral part of it?
So I can design an airfoil with a shape which mimics the gurney flap (or an interceptor) and nobody could say anything about it. It is not an interceptor, it is the airfoil's shape - as odd as it could be. If we assume that this is legally possible, than an interceptor would have a pretty big effect on the pressure field around the foil.
Since one picture is worth a thousand words, I have prepared this comparative graph:
View attachment 84873
It shows two identical airfoils, the above one in clean configuration, the bottom one with a small (1.5% of the chord) gurney flap set at 65°.
For the same lift coefficient (0.7 approximately) the foil with a gurney works at a much lower angle of attack, has a much lower peak pressure coefficient (Cp) and the distribution of Cp along the chord is nearly flat and low-value. A low (absolute value of) Cp means that cavitation (and a ventilation too) is delayed for a given speed, thus increasing the foil efficiency.
For the same angle of attack, a foil with a gurney flap has a considerably higher Cl (i.e. produces more lift), at a very small drag expense.
I see the most value of gurney at low speeds, where a high lift coefficient is required for a rapid take-off to a foiling mode. At high speed, close to maximum speed, a foil with an interceptor will produce a higher pitch-down moment and will hence require more balancing negative lift by the rudder elevator. That is a straightforward drag. The final result, in terms of maximum speed, would be the sum between less drag due to delayed cavitation and ventilation, and more drag due to the elevator working harder. Hard to say more with no real-world telemetry data from the boats.
A few remarks:
- Please note that when I say "low Cp", it is referred to its absolute value, |Cp|. Example: |-2| = 2 and |-4.5|=4.5
- Also, please note that these Cl values are not related to the actual AC72 foil data (we don't even know for sure whether it was the solution used by the Oracle), but serve to make a visual explanation of what the gurney flap does to the pressure field around the foil.
- Furthermore, this is a numerical analysis made with a computer software, hence based on a mathematical model of airfoil aerodynamics. So don't take the numerical values shown in the graph as absolute truth. I wouldn't be surprised to find out there's a difference of 10-15% respect to experimental or measured values, in this range of angles of attack.
- Finally, the above graphs show a small-scale saw-toothed irregularities, which is probably due to a numerical instability coming from the very high Reynolds number used for the calculations. But for the purpose of a qualitative comparison, they are more than adequate.
Cheers
Great stuff here-thanks Slavi!