[QUOTE=TangoKilo;22956646]
Quote:
Originally Posted by markdrela
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