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Old Oct 11, 2012, 03:34 PM
markdrela is offline
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Cambridge, MA USA
Joined May 2001
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[QUOTE=TangoKilo;22956646]
Quote:
Originally Posted by markdrela View Post
Thrust = mass_flow_rate * (Vexhaust - Vflight)
Mark, how did you arrive at this equation?
Integral Momentum Theorem applied to a control volume surrounding the propeller.
Pretty standard stuff.
http://web.mit.edu/16.unified/www/SP...es/node86.html
section 11.7.2
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