Sorry can't help, I have no close up photos, just me posing at the cockpit. However there are quite a few of this ex-USSR aircraft in the West. There may be one at your nearest airfield you can look at.

The formula for calculating a CG position and hence the degree of pitch stability is

0.25-staticmargin+(0.25*(aspectratio^0.25)*((tailarea*t ailmoment)/(wingarea*MAC)))

where static margin varies between 0.1 and 0.2 and describes the amount of pitch stability desired expressed as a relationship of the CG to the Neutral Point.

Pitch stability is what determines if a plane pulls the nose up as speed increases. Note that there is no term in the equation for the wing section or its moment pitch co-efficient. The wing section has no effect on stability. What matters is the tail volume ratio, the position of the neutral point and the CG in relation to the neutral point. The further forward the CG is then the greater the longitudinal dihedral required, and the greater the speed stability of the aircraft.

Harry