It depends on the technology used. P&W’s PYBBN and GE’s AVEN nozzles add less than 75 kg compared to conventional nozzles. The use of fluid vectoring can weigh even less.
DJ, any ideas on cost of the systems?
Guys, any more suggestions on calculating thrust vs. altitude and SFC as a function of power, speed & altitude?
Also, anyone knows how much a 3-D thrust vectoring nozzle such as the one on a Eurofighter might cost?
I thought the EJ200 made thrust in the 22,000lbs class? Much like the GE F-414 in the Super Hornet. How similar are the two designs?
By 2010-2015, it will be 27klb. Go to the middle of this page
Thrust is proportional to mass flow which is dependent upon density.http://www.grc.nasa.gov/WWW/K-12/airplane/thrsteq.html
That is exactly the problem. There are some approximate expressions on this site: http://www.adl.gatech.edu/classes/dci/engines/dci05.html but I am not sure how accurate these expressions are.
The RB199 isn’t a good performer in high altitude, perhaps the EF200 isn’t one at low altitude.
I’m referring to the EJ200, not the RB199. The stage 2 modification will feature 27,000lbf of thrust AB and 23,000lbf of thrust dry.
I am assuming this is hypothetical? Phil 🙂
I am assuming this is hypothetical?
Phil 🙂
In a sense, it is. It is impossible to create a precise model because actual conditions will change.
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