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Unformatted text preview: t will be given by V ( t ) = V + V e ln M M ( t ) -g [ M-M ( t )] ˙ m R where M(t) is the mass of the system at time t. Note that the pressure of the gas at the rocket exit plane, p e , will not be zero as it is in the ambient space, since the rocket exhaust is supersonic and hence the pressure at the exit is in balance with the ambient pressure. The answer given above neglects the effect of the exit plane pressure on thrust....
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This note was uploaded on 02/27/2012 for the course MECHANICAL 2.25 taught by Professor Garethmckinley during the Fall '05 term at MIT.
- Fall '05