f14_ps04_spring04 - Spring 2004 Spring 2004 Unified...

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Unformatted text preview: Spring 2004 Spring 2004 Unified Engineering Engineering F14. An aircraft is flying at speed V� , in an atmosphere with p� , and �� . a) What is the flight Mach number M� ? Give in terms of the quantities above. b) Determine the stagnation pressure po at the nose of the aicraft in two ways: i) The exact full compressible equation. ii) The incompressible Bernoulli equation, pretending � = �� is constant. Plot po /p� versus M� for the two equations. Also plot the “Bernoulli error” (po /p� )exact − (po /p� )Bernoulli versus M� . What would you judge to be a reasonable upper Mach limit on the validity of the Bernoulli equation? ...
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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.

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