The neutral point on a symmetric airfoiled fin is at 25%MAC. The suggestion to have a quarter of the area in front and 3/4 behind is not a good suggestion. That is right around the neutral point. Plus, the neutral point shifts forwards as angle of attack increases. At 25% the results are unstable. You want more area to be behind than that just so the fin weathercocks to the freestream. Just to note, it isn't area in front or behind the pivot, it is pivot location compared to percentage of the MAC (mean aerodynamic chord) and you might want to bias away from some of the area right next to the rocket body as the airflow is different there.
https://aviation.stackexchange.com/...tre-of-pressure-aerodynamic-centre-and-neutra
As you get into the transonic region the neutral point will shift, and continue shifting as the rocket goes faster.
Another issue which I think wasn't mentioned is everyone seems to be applying a statics analysis to a dynamics problem. Think about materials flex, time lag on response due to inertia and non-steady flow, and potential resonances and potential instabilities. You might find those pivoting forward fins at certain speeds can force the rocket into coning or other bad behavior.
Gerald