f14_ps04_spring04

f14_ps04_spring04 - Spring 2004 Spring 2004 Unified...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
This is the end of the preview. Sign up to access the rest of the document.

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? ...
View Full Document

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.

Ask a homework question - tutors are online