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at 0.402lbs/s at 22psi with an efficiency of 70% and a turbine efficiency of 78%, I'll have a turbine outlet temp of 679C consuming a require pressure ratio of 1.76. I've calculated that nozzle efficiency is around 90% for a PR of 1.36. Nozzle exit temps at 617C at a velocity of 1256ft/s and a gas density of 40.3cuft/lb. f=ma shows about 15.7lbs of thrust without the afterburner. The afterburner will probably augment this value by around 50% for a total of around 23.55lbs of static thrust. Not a whole lot, but will be something usable to move me around a little bit. :) Of course, this is just the theoretical calculation - I'll have to setup a fish scale and a roller board to test the actual thrust to see how close my calculations are.
[ ashspecz.com ] [ agpowers@bellsouth.net ] Enthusiasts soon understand each other. --W. Irving. Are you an enthusiast? If you are out to describe the truth, leave elegance to the tailor. Albert Einstein
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