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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
. 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.
- Fall '05