I'd stick to using tried and true airfoils designed by others that already know how to optimize the shapes to achieve the best pressure distributions and lift curves. It's not like there isn't about a bazillion options.

The first step would be to get access to Xfoil with a nice interface. That would be to download Profili2 and pay the pittance he asks for unlocking the advanced features so you can gain access to the Xfoil portion. From there it's about trying to determine what lift coefficient you'll be needing in the turns. Find an airfoil with a low drag Cd at a Cl of 0 but that has the best Cl with minimum Cd. You'll also need to take your chord and figure out the average speed range for your racing class to find the Reynolds number you're running with. Keep in mind that goes down a little thanks to extra drag in the turns.

Once you do this look at the lift drag polars for the Selig 6061. It has the sort of polars I'm talking about. A very consistent drag polar from Cl=0 to up around Cl=.8 with only a slight increase at it goes to Cl=.9 and then it gets draggy. On the straights you'll be running at extremely close to a Cl = 0 and in the high G turns at a Cl = around 0.8 to 1.0. You want to pick an option that fits with your rules and yet has an even and low a drag polar for the Re in question yet that extends up to as high a Cl as you can get without getting draggy at the Cl = 0. At high speeds and in level flight your Cl may be as low as .01 or even less.

You can play with what your Cl will be by learning to use a handy little tool called Foilsim. A quick google on the name will take you to the NASA site with Foilsim. YOu may need to install or update your Java to run it.