J-20 5th Gen Fighter Thread VI

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Figaro

Figaro

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Tirdent said:
Thanks!

There are a lot of significant digits, but nothing that would immediately mark them as false (other than dry sfc being rather optimistic perhaps). OTOH, what does the mass flow in kg/s refer to in the specs you posted - seems way too low for total engine mass flow and still far too low for core mass flow? Bypass mass flow (but you say it's the core) would be possible I suppose? Is there any info on the architecture (stage counts, essentially)?
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30 kg/s is the core's corrected airflow. Regarding the information earlier, the turbine inlet temperature is pretty off the mark at 1750K, which is around the WS-10's inlet temperature of 1747K. The TWR of 8.86 also appears false given the TWR 10 requirement for fourth generation engines set by the PLAAF. And once again, having extremely precise figures such as 161.865 kN or 1862.3 kg should be a screaming red flag.
 
L

latenlazy

Brigadier
Tirdent said:
Thanks!

There are a lot of significant digits, but nothing that would immediately mark them as false (other than dry sfc being rather optimistic perhaps). OTOH, what does the mass flow in kg/s refer to in the specs you posted - seems way too low for total engine mass flow and still far too low for core mass flow? Bypass mass flow (but you say it's the core) would be possible I suppose? Is there any info on the architecture (stage counts, essentially)?
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As I recall those figures were first seen in a comment that also made some rather dubious claims, like that there was going to be a STVOL stealth fighter in 2013. I don’t think we were ever able to trace the source of those numbers beyond that.
 
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Tirdent

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Yes, turbine inlet temperature did seem rather low for a next generation engine, though I'd expect the basic WS-10 (as opposed to the more recent models) wasn't quite that high initially?

Corrected flow sounds plausible - HPC inlet being hot & high pressure, there would definitely be a significant factor on actual mass flow. I take it 6.0 is HPC pressure ratio? How many stages are there, did the earlier article get that right?
 
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Klon

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Tirdent said:
Yes, turbine inlet temperature did seem rather low for a next generation engine, though I'd expect the basic WS-10 (as opposed to the more recent models) wasn't quite that high initially?

Corrected flow sounds plausible - HPC inlet being hot & high pressure, there would definitely be a significant factor on actual mass flow. I take it 6.0 is HPC pressure ratio? How many stages are there, did the earlier article get that right?
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If you want to, go through maya's posts on this forum (just enter the username in the right search field). He is the only insider (that I know of) to have posted on this forum. Most of your questions probably won't be answered, but it's still pretty interesting.
 
Figaro

Figaro

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Not sure if J-10's engine is also Taihang ...
9foLBd2.jpg
 
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J

jobjed

Captain
Figaro said:
Looks like the J-10's engine is also Taihang ...
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Ehhh... I think it looks like an AL-31FN.

WS-10s have a stubbier nozzle and aren't as black and instead more silvery.

It's actually impressive how many of the aircrafts' key features he managed to include in the paintings, from the undercarriage anchoring equipment used for full afterburner tests, the luneburg lenses under the J-20s, the second antenna on the J-10C's spine, the extra trapezium on top of the J-10Cs' vertical stabiliser, to the colouring of the afterburner trail of the J-20 taking off. The title of the piece, 太行之巅-双龙 (Taihang precipice - dual dragons) also affirms the existence of two WS-10 J-20s.

All in all, props to the artist.
 
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