AAE 334 Fall 2011, Homework 25 SOLUTIONS
Due Wednesday, November 16 at the beginning of class.
1.
Compute manually (not using the
PM_
Matlab functions) the pressure after a 10 degree
expansion corner if the upstream flow is at Mach 2 and pressure of 100 kPa.
2.
Compute manually (not using the
PM_
Matlab functions) the temperature ratio,
1
2
/
T
T
for the flow in the first question.
3.
Using the
PM_
Matlab functions compute the pressure on the upper surface of a flat
plate airfoil at Mach 2 in units of upstream pressure.
Plot the pressure on the upper
surface and the lower surface pressure from HW 24 versus angle of attack.
Besides
explaining what you did and why, hand in a hard copy of the mfile and your plot.
Part 1: (see Example 9.9 in the text too) From the PrandtlMeyer table, we see that a Mach 2
flow has a PrandtlMeyer angle of 26.38
o
.
Add on the ten degree turning angle and the new
PrandtlMeyer angle is 36.38
o
.
Nearest value to a PrandtlMeyer angle of 36.38
o
is
M
2
=2.40
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 Fall '09
 COLLICOTT
 Fluid Dynamics, Aerodynamics, Shock wave, PrandtlMeyer angle, PM_ Matlab functions

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