My examples are all for a symmetrical section (which all real airplanes use:-) which is easier to analyze since we don't have a good natural feel for wing moments due to camber.

Certainly the Cmo of the NACA 2424 is not too much because it looks just a little fatter that the airfoils that Kasmiriski (did I spell it right?) used to use in his Taurus. His airplanes flew with very little elevator trim being required.

Figure 1 and 2 are OK.

Figure 3 is for the CG at the quarter cord. Of course with the lift at the CG at 25% there is no wing moment for the tail to take care of. So the elevator must be deflected enough to overcome the up load on the tail at angle of attack. It requires a really bing deflection to the point that a lot of planes require flying around with full aft stick when rigged that way.

Figure 4 is screwed up pretty badly unless he is talking about increments. If he is saying that the increment due to camber requires an incremental tail load in the down direction - OK. But increments only.

Figure 5 is close but he has assumed the the negative pitching moment due to camber is equal to the lift times its moment arm. Ain't necessarily so. If you have camber (and perhaps some flap) just right it can happen but it is not a given.