You'd better write in English, it's a challenge to translate it back in hope to understand what you mean
About roll rate, I didn't find anything valuable for you. I've got heaps of data for low airspeeds (<500 km/h) and not much more. MiG-23UB Flight manual (at least the parts I've got) doesn't have the data.
I don't know if this is of any help for you, but the only real
data I found (sweep angle 45°) is the derivative of the roll rate by the control deflection. This derivative indicates control efficiency.
Roll is controlled (mainly) by differential deflection of the horizontal stabiliser (MiG-23 doesn't have ailerons; spoilers are used at low sweep angle, but this is taken into account for the derivatives). The deflection angle is calculated as the half difference between the angles of the left and right halves of the stabiliser. That is, if the stabiliser is trimmed at -5°, for the effective roll deflection of, say, 3° (positive deflection for roll left), the left half will be set at -8° and the right half at -2° (negative sign means aircraft nose up elevator deflection).
Maximum effective roll deflection at low sweep angles is ±10° (or until physical limit is reached - this may happen at high elevator
deflections, as this is the same control surface).
Now, the (maximum, i.e. static) roll rate is calculated as the _(roll_control_derivative)*(deflection)_. The dependency may not
be that linear at extreme conditions, but generally shows very good linear behaviour in normal (subsonic) regimes.
In turn, the derivative depends on airspeed. For the airspeeds I have the data for, it is highly linear as well. You can interpolate (and extrapolate up to, I think, ~800 km/h) it to obtain the values for any airspeed using two base points:
-0.062 [rad/s/deg] for V=300 km/h and -0.1 [rad/s/deg] for V=400 km/h. Note the units:
the resulting angular velocity is in rad/s, but the derivative reflects the deflection in degrees.
That all means, that for maximum deflection of -10° the maximum roll rate at 400 km/h will be 1 rad/s (~57 deg/s). And about 2.5 rad/s (140 deg/s) at 800 km/h.
Also note that the airspeed here is the indicated
airspeed; that is, equivalent to zero altitude dynamic pressure. For zero altitude, it is the same as true airspeed; at higher altitudes, the true airspeed is higher.
As for Su-15, I don't have anything at hand.
Администраторы (всех видов), погодите пока переносить в англоязычный, а то товарищ не найдет