mae 422 Gas Dyna mics Spring 2006
EXAM 1
1. The local conditions after a normal shock in air, ( = 1.4 ), are
M = .4512, p= 5 atm, T= 370 K. What is the Mach Number and velocity
before the normal shock ? Sketch a temperature entropy diagram for this
proces
Problem Set 7 (PS 7) Due Tuesday March 7
7.1 Air is flowing in a duct configured like Figure 4.19 in the text with 1 =10 degrees,
2 = 20 degrees and with Mach Number of 3 in the flow approaching the corner. What
is the temperature, pressure and velocit y
Chosen problems and their final solutions of Chap. 2 (Waldron)- Par 1
1. In the mechanism shown below, link 2 is rotating CCW at the rate of 2 rad/s (constant).
In the position shown, link 2 is horizontal and link 4 is vertical. Write the
appropriate vect
MATH REVIEW
for Textbook
Kinematics, Dynamics, and Design of
Machinery
by
K. J. Waldron and G. L. Kinzel
1996-99 by K. Waldron and G. Kinzel
Department of Mechanical Engineering
Math Review
1 Coordinate Systems
Three types of coordinate systemsare commonl
CHAPTER (12)
COMPRESSIBLE FLOW
SOLVED PROBLEMS
09/12/2010
Dr. Munzer Ebaid
1
SUMMARY
c = kRT
1. Speed of Sound:
p Isentropic Process (Adiabatic reversible)
c =
S
2
2. Mach Number:
3. Total Temperature: Tt = T 1+ k 1M 2
2
(Adiabatic Process)
4. Total P
normalshock_02
Stagnation pressure and temperature probes are located on the nose of a supersonic aircraft at 35,000 ft
altitude. A normal shock stands in front of the probes. The temperature probe indicates T0 = 420 F behind
the shock.
a. Calculate the M
cen84959_ch17.qxd 9/15/06 6:08 AM Page 849
Chapter 17
COMPRESSIBLE FLOW
F
or the most part, we have limited our consideration so
far to flows for which density variations and thus compressibility effects are negligible. In this chapter we lift
this limita