Ok, here is a quote from book by P.Butowski: “Vertical thrust of R-79 engines with reaction control puffers (end of wingtips and tailbooms) is 137.3kN (14000kG) and after considering loses – 122.6kN (12500kG)”

The nozzle F135 – a copy of the nozzle engine R-79
Afterburner thrust engine 17876 kgs (vertical mode) / 19507 kgs = 0.92 – a loss of power.
R-79 15500 kgs * 0.92 = 14260 kgs

The nozzles of the engines are identical! Therefore, the power loss in these nozzles are close! That’s all I wanted to say

So what is the difference between Mig-29M2 and Mig-35?

The MiG-29M2 is a cheap option, radar ЖуК-МЭ slot antenna

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I think that American presidents do not decide anything. It is a farce-a figure

Yes, hundreds of western advisors embedded in ISIS, where do you get your news “I hate the west and NATO is going to invade Russia Weekly”?

It is not even discussed, the West will invade the territory of Russia thousand years.

Guess it means, Russia does not have enough force projection in and around Syria, to deal with this new situation in Palmyra.

The Coalition has released terrorists from Mosul, and they came to Palmyra. The Coalition supports terrorists.

This affects the power loss?
The BS company has built a flying plane with the nozzle?

All sources give the maximum takeoff weight in vertical mode as 15800kg so I don’t think there is much argument with this. Also, the thrust of R-79 in vertical mode was closer to 12500kG

Engine R-79B-300
afterburner thrust horizontal 15500 kg
afterburner thrust vertical 14000 kg
Maximum horizontal thrust 10977 kg (according to other sources 9000 kgf)
cruising fuel consumption 0.66 kg / kgf * h

RD-41 engine
maximum thrust of 4100 kgf
fuel consumption of 1.4 kg / kgf * h

takeoff thrust
14000 kgs + 2 * 4100 kgs = 22200 kgs (kgs – килограмм-сил / kilogram-force)