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Old Oct 10, 2012, 04:23 PM
TangoKilo is offline
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[QUOTE=nristow;22965239]
Quote:
Originally Posted by TangoKilo View Post

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.
Well, I see F = d(mv)/dt and I see F = m.a +mdot.v

but I don't see Thrust = mass_flow_rate * (Vexhaust - Vflight)

Can you briefly explain how you have rewritten Newton's second law?
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