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Old Oct 10, 2012, 03:41 PM
nristow is offline
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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?
It's part of the continuity equation, a rewriting of Newtons second law, you can see here:

http://en.wikipedia.org/wiki/Mass_flow_rate

Near the bottom of the page, under usage.

The equation Mark gave ignores the acceleration term.

The velocity term gives you a linear relationship, from maximum attainable thrust at 0 airspeed, down to zero thrust at whatever the exhaust velocity itself is.
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