Kim gives a good method to use for determining these relationships. At the risk of being scewered for using math outside of the engineering thread, there's a simple mathematical way to determine a close approximation.
First, consider that the nose has to be long enough to mount the engine, and tank comfortably.
Second, determine the wings CG at the MAC.
Third, measure the distance from the CG forward to the approximate center of mass of the engine,prop, and spinner.
Get the accurate weight of the engine, prop, and spinner.
Do the same for the tank, and also the landing gear.
Estimate the total weight of the fuselage itself, and figure that about 25% of that weight will be forward of the CG.
This now means that 75% of the fuselage weight will be aft of the CG.
Figure the approximate center of masses for the portions of the fuse, on either side of the CG, and this will be your length.
Estimate the weight of the stabs,, rudder, and elevators.
The formula looks like this.
(A*L1)sq'd +(B*L2)sq'd +(C*L3)sq'd + (D*L4)sq'd = (E*L5)sq'd - (F*L6)sq'd
Plug in the weights, and lengths that are associated with each other. Work the simple algebra, and you'll be left solving for L6, the legnth to the centerr of mass for the stabs and elevators. Your tail moment. Be sure and remove the sq by using the sq root function.
This will get you very close to a balanced condition, as long as your actual weights are close to what you estimated.
You can work even closer by inserting more component weights if you want to, but the above will usually be good enough when all conditions are considered.
Since I've always been math challenged, I may have made an inadvertant error. If so, I'm sure that someone will correct me.