Perhapbs I should clarify. In comparison to other turbojets, the ‘raw’ figures on the R-35 look very impressive. Same weight as the J-79 but much more powerful. I’m aware that the J-79 is an earlier generation engine, but then if you compare the later models with what is essentially ‘ a warmed over R-29’…I also see that it is smaller than the R-29, so if anybody could explain if they are essentially the same engine I’d appreciate it.
By best, I didn’t mean just raw thrust. I’m aware the West started concentrating more on turbo fans in the sixties, so the Sov Union perhaps developed the turbojet a little further. The J-75 was a big beast weighing in at around 6000lbs for less thrust. It was an earlier engine as well. The olympus was not used operationally on a jet fighter to my knowledge. As also explained earlier, the different models used in the Vulcan and those meant for the TSR2 were very different engines.
I’m trying to establish the various figures of TBO, SFC etc. to find out if the increase in thrust achieved was a lower life, or more advanced design and materiels. I also would like to know if the R-35 was installed in lets say a Mirage F1, would it supercruise? The external dimensions of the R-35 are a lot smaller than the Atar…With a renewed emphasis on supercruise, wouldn’t a turbojet make sense as opposed to a turbofan?
Either way, it is a very impressive turbojet, and probably the most powerful ever put into a production fighter jet.
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