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 horizo
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 in
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 Coordina
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 Temperat
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 effe
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
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