In a sinle post let me know: wing span , chord, taper ratio, the airfoil used, the weight of the model loaded and unloaded, the expected leingth from quarter chord of the wing to quarter chord of the tail, the airfoil for the tail, incidence of the wing, and I will compute for you an accurate cg location, horizontal tail planform, tail incidence, and give you an accurate static margin for your aircraft, based on "sport plane characteristics" as for the verticle, your on your own.
Nmking09

oh and the reason that some models pitch up with flaps is not due to the inreased lift, it is mostly due to the change in the downwash angle, this changes the effective incidence of the horizontal causing a trim change. The actual pitching moment due to flaps is nose down, just like a highly cambered airfoil. This changing of downwash and upwash angles is why you don't see many canards with flaps.