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Unformatted text preview: 2.5. BRAYTON 51 Solving for the thrust force, neglecting the small differences in pressure, one gets, F = m ( v 5 v 1 ) . (2.294) The work done by the thrust force is the product of this force and the air speed, v 1 . This gives | W p | = | F v 1 | = | m ( v 5 v 1 ) v 1 | . (2.295) Now the efficiency of the cycle is a bit different. The net work of the turbine and compressor is zero. Instead, the propulsive efficiency is defined as p = Propulsive Power Energy Input Rate = | W p | | Q H | , (2.296) = | m v 1 ( v 5 v 1 ) | m | ( h 3 h 2 ) | . (2.297) Note the following unusual behavior for flight in an ideal inviscid atmosphere in which the flow always remains attached. In such a flow DAlemberts paradox holds: there is no aerodynamic drag. Consequently there is no need for thrust generation in steady state operation. Thrust would only be needed to accelerate to a particular velocity. For such an engine then the exit velocity would equal the entrance velocity:...
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- Fall '11