AAE 334 FINAL EXAM QUESTIONS WITH CORRECT ANSWERS LATEST UPDATE 2026
LECTURE 26 - Answers 26
If you take a supersonic stream and turn it at an angle, what will you generate? How can you make
this effect stronger? - Answers An oblique shock, a bigger turning angle
Velocities across the face of a shock (tangential velocity) dont change across the shock. - Answers
True.
What is the theta - Beta - M chart used for? - Answers theta - deflection angle
beta - shock wave angle
M - Mach upstream of shock
If you have 2 out of three of these variables, you can use the chart to solve for the third unknown
parameter.
As deflection angle increases, shock wave angle increases for a weak shock. - Answers True. (See TBM
charts)
Larger Mach numbers are associated with larger deflection angles and relatively lower shock-wave
angles. - Answers True. (See TBM charts)
If we try to turn a supersonic free-stream beyond its max sonic limit, what happens to the shock? -
Answers It becomes a strong detached shock.
The upper limit of the TBM chart when the shock wave angle approaches 90 degrees is considered.... -
Answers a normal shock
A low back pressure is associated with a strong shock. A high back pressure is associated with a weak
shock. - Answers Incorrect.
Low back pressure = Weak shock
High back Pressure = Strong Shock
A weak shock solution is usually associated with a supersonic flow behind it, but can have a subsonic
flow behind it if we are close to the maximum turning angle. - Answers True.
A strong shock solution always has supersonic flow behind it. - Answers False, it always has subsonic
flow behind it.
LECTURE 27 - Answers 27
You will generally see a much larger total (especially stagnation) pressure loss going through a normal
shock than an oblique shock. - Answers True.
If the turning angle is too large for the reduced Mach number behind an oblique shock, what is the
result? - Answers A Mach Reflection / Slip Line
There is no reflected wave if the upper wall follows the new flow direction. - Answers True
LECTURE 28 - Answers 28
Supersonic flow over wedge is uniform and is parallel to surface of wedge. Supersonic flow over cone,
flow is not uniform behind shock, shock wave angle is smaller than angle of cone. - Answers True
Conical flow properties only only depends on the angle of the center line of the oblique shock that is
formed. - Answers True.
Downstream of shock for a wedge: Curved streamlines and nonuniform flow that approaches surface.
Downstream of shock for a cone: Straight streamlines and uniform flow. - Answers False, they are
switched.
Which is stronger, wedge or conical shock? - Answers Wedge is much stronger
For P-M Expansion, the following properties change:
M2 > M1
rho2 < rho1
p2 < p1
T2 < T1 - Answers True.
An expansion fan is an isentropic process since it occurs non incrementally. - Answers false, it is
isentropic but the change is slow
LECTURE 29 - Answers 29
Supersonic flow expanding over the airfoil and being compressed through a shock on the bottom of
the airfoil is where lift comes from for a supersonic airfoil. - Answers True
LECTURE 26 - Answers 26
If you take a supersonic stream and turn it at an angle, what will you generate? How can you make
this effect stronger? - Answers An oblique shock, a bigger turning angle
Velocities across the face of a shock (tangential velocity) dont change across the shock. - Answers
True.
What is the theta - Beta - M chart used for? - Answers theta - deflection angle
beta - shock wave angle
M - Mach upstream of shock
If you have 2 out of three of these variables, you can use the chart to solve for the third unknown
parameter.
As deflection angle increases, shock wave angle increases for a weak shock. - Answers True. (See TBM
charts)
Larger Mach numbers are associated with larger deflection angles and relatively lower shock-wave
angles. - Answers True. (See TBM charts)
If we try to turn a supersonic free-stream beyond its max sonic limit, what happens to the shock? -
Answers It becomes a strong detached shock.
The upper limit of the TBM chart when the shock wave angle approaches 90 degrees is considered.... -
Answers a normal shock
A low back pressure is associated with a strong shock. A high back pressure is associated with a weak
shock. - Answers Incorrect.
Low back pressure = Weak shock
High back Pressure = Strong Shock
A weak shock solution is usually associated with a supersonic flow behind it, but can have a subsonic
flow behind it if we are close to the maximum turning angle. - Answers True.
A strong shock solution always has supersonic flow behind it. - Answers False, it always has subsonic
flow behind it.
LECTURE 27 - Answers 27
You will generally see a much larger total (especially stagnation) pressure loss going through a normal
shock than an oblique shock. - Answers True.
If the turning angle is too large for the reduced Mach number behind an oblique shock, what is the
result? - Answers A Mach Reflection / Slip Line
There is no reflected wave if the upper wall follows the new flow direction. - Answers True
LECTURE 28 - Answers 28
Supersonic flow over wedge is uniform and is parallel to surface of wedge. Supersonic flow over cone,
flow is not uniform behind shock, shock wave angle is smaller than angle of cone. - Answers True
Conical flow properties only only depends on the angle of the center line of the oblique shock that is
formed. - Answers True.
Downstream of shock for a wedge: Curved streamlines and nonuniform flow that approaches surface.
Downstream of shock for a cone: Straight streamlines and uniform flow. - Answers False, they are
switched.
Which is stronger, wedge or conical shock? - Answers Wedge is much stronger
For P-M Expansion, the following properties change:
M2 > M1
rho2 < rho1
p2 < p1
T2 < T1 - Answers True.
An expansion fan is an isentropic process since it occurs non incrementally. - Answers false, it is
isentropic but the change is slow
LECTURE 29 - Answers 29
Supersonic flow expanding over the airfoil and being compressed through a shock on the bottom of
the airfoil is where lift comes from for a supersonic airfoil. - Answers True
