I've seen some analyses of US types that included the wing area, flap area, aileron area, vertical tail area, rudder area, horizontal tail area, and elevator area, but have not seen a specific analysis of the Bf 109, not have I looked for one.
Usually there are some rather standard aerodynamic formulas for calculating the tail area required and the area of the surfaces and I never really analyzed the Bf 109 because, although I used to think the tail areas might be small, I also never heard any pilot complaints about controlability except for lack of trim tabs on rudder and aileron and the stiffening up of the control surfaces at speed. I never saw anything in a combat or flight report that made me think it might be anywhere close to the edge of what might be required.
In fact, if the flight reports are to be believed, the Bf 109 has probably the most benign stall characteristics of all the WWII fighters, making me feel that an analysis of this would be a waste of my time ... the areas are sufficient or there would be complaints about the stability or controlability. Since there are none to speak of, I never thought about it.
The first requirement would be to dig up specification that show the areas of the flying surfaces and control surfaces. We already know the power installed but, again, I've never seen the areas broken out before for the Bf 109... though since I wasn't looking for it, I may have come across it and just never considered it as something to save.
If I were a betting guy, I'd bet Bill has these areas. I also bet he won't find the Bf 109 areas too small relative to standard area percentages for a WWII fighter since the Bf 109 was an EXCELLENT fighter design and probably ranks at the top all-time for effectiveness. The Bf 109 was used to shoot down a LOT of enemy airplanes, so it isn't exactly a flying mistake.
In the design of RC models, it is pretty standard to have the area of the horizontal surface come out to 0.7 ~1 = (Sw/St)* (L/MAC) where Sw is wing area, St is tail area, L is the distance between the center of pressure of the wing and tail, and MAC is mean aerodynamic chord. You choose about 0.7 for more maneuverability and about 1 for more stability.
For the vertical stab area, you choose in the neighborhood of .05 = (Sw/St) * (L/b) where b is span.
The function of the aircraft must be taken into account. A fighter is NOT an aerobatic plane nor is it an airliner, so the designer starts with some designs and refines his numbers as he goes on ... depending on how the real aircraft designs fly with regard to intended purpose. If he designs a fighter that flies more like an airline, then he'll change the size of the surfaces to compensate.
It's a bit more involved with full scale aircraft but, with RC's ... the numbers fall into a small group depending on the desired function of the plane.
I have Hoerner's lift book in pdf format, but it's 65Mb in size and not practical to reproduce in here. I also haven't read it much for a couple of decades or longer. If I were to go back into aerodynamics again, it would be for a good reason ... that is, a project.