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Unformatted text preview: [Note: To solve this problem you will have to use relationships from thermodynamics (steady flow energy equation) and fluid mechanics (compressible flow relations). These can all be found in the Unified Propulsion notes (Chapters V and VI). Most of the relations are written in terms of the exit Mach number, Me. To find this you will have to try several values of Me in the relationship for A*/Ae until the equation gives you the same ratio as given in the problem statement.]...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
 Fall '05
 MarkDrela
 Propulsion

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