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Nov26-12, 06:20 PM
P: 22
How would the equation look if instead of knowing the effective exhaust velocity we knew the force the exhaust was exerting on the rocket.

The equation is:

[tex] \Delta V = v_e * ln(\dfrac{m_0}{m_1}) [/tex]

would [tex] \Delta V [/tex] still be proportional to the log of the initial mass over the final mass?
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