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Apr 16, 2019 at 17:16 comment added Peter Kämpf @Pheric: The pressure must be the static pressure. Of course, total pressure should be constant, apart from viscous losses. For subsonic flow this makes sense.
Apr 16, 2019 at 12:40 comment added Pheric In figure 1.15, why is pressure decreasing with velocity increasing before the nozzle / choke point? This goes against everything I know.
Apr 14, 2019 at 13:57 history edited Peter Kämpf CC BY-SA 4.0
exit flows can be supersonic, after all.
Aug 22, 2015 at 5:09 comment added Peter Kämpf @L3R5: You're right, I never noticed that the RD-36 had no variable nozzle. The NK-144 used on earlier Tu-144s, however, used a regular con-di-nozzle. I suspect that the RD-36 could shift the central cone forward and backward to adjust for dry and wet states, but I could find no information about this.
Aug 22, 2015 at 1:39 comment added Kurt Tank Correct me if I'm wrong but the supersonic Tu-144 didn't have a variable nozzle because it was designed around a certain cruise speed. The nozzle shape was most effective at that speed and since the aircraft didn't spend much time flying outside of that speed, nothing more complex was needed. Same principle for subsonic jetliners: they are optimized to fly at a certain speed, so they don't need that much flexibility.
Nov 21, 2014 at 22:25 vote accept fooot
Nov 14, 2014 at 11:42 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 22:23 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 21:44 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 21:19 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 21:13 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 21:02 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 20:51 history edited Peter Kämpf CC BY-SA 3.0
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Nov 13, 2014 at 20:44 history answered Peter Kämpf CC BY-SA 3.0