Velocity of the fluid at the nozzle exit

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Reference no: EM13711524

Show that the thrust developed by a stationary rocket motor is F = rho*A*U^2 + A(p- p_atm) where p_atm is the atmospheric pressure, and p, rho, A, and U are, respectively, the pressure, density, area, and velocity of the fluid at the nozzle exit.

Reference no: EM13711524

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