| class |
date |
subjects |
reading |
cwr |
prob |
due |
| 01 R |
Sep 05 |
Intro; Reynolds transport theorem |
1.1-6 |
C-01 |
P-01a |
|
| 02 F |
06 |
Conservation of mass, momentum, energy |
1.7--9 |
C-02 |
P-01b |
|
| 03 M |
09 |
Second law; equations of state; 1-D flow |
1.10-12 |
C-03 |
P-01c |
|
| 04 T |
10 |
Wave propagation; velocity of sound |
2.1-3 |
C-04 |
P-01d |
|
| 05 R |
12 |
Sub- and supersonic flow; mach number |
2.4-6 |
C-05 |
P-01e |
|
| 06 F |
13 |
Equations of motion (isentropic perfect gas); varying area channels |
3.1-3 |
C-06 |
P-02a |
P-01 |
| 07 M |
16 |
Stagnation properties, tabular data |
3.4 |
C-07 |
P-02b |
|
| 08 T |
17 |
Isentropic flow in a converging nozzle |
3.5 |
C-08 |
P-02c |
|
| 09 R |
19 |
Isentropic flow in a converging-diverging (CD) nozzle |
3.6-7 |
C-09 |
P-02d |
|
| 10 F |
20 |
Formation of a normal shock; equations of motion |
4.1-3 |
C-10 |
P-03a |
P-02 |
| 11 M |
23 |
Equations of motion for a normal shock, tabular data |
4.3 |
C-11 |
P-03b |
|
| 12 T |
24 |
Moving normal shock waves |
4.4 |
C-12 |
P-03c |
|
| 13 R |
26 |
Reflected normal shock waves |
4.5-6 |
C-13 |
P-03d |
|
| 14 F |
27 |
Performance of CD nozzles, back pressure |
5.1-2 |
C-14 |
P-04a |
P-03 |
| 15 M |
30 |
Optional review day |
|
C-15 |
|
|
| 16 T |
Oct 01 |
Exam I: Reynolds Transport & Shocks |
|
|
|
|
| 17 R |
03 |
Supersonic wind tunnels |
5.3 |
C-17 |
P-04b |
|
| 18 F |
04 |
CD supersonic diffuser |
5.4 |
C-18 |
P-05a |
P-04 |
| 19 M |
07 |
Shock tube; one-dimensional unsteady flow |
5.5 |
C-19 |
P-05b |
|
| 20 T |
08 |
Oblique shock waves; equations of motion |
6.1-2 |
C-20 |
P-05c |
|
| 21 R |
10 |
Weak and strong shocks; oblique shock reflections; conical shock waves |
6.2-4 |
C-21 |
P-05d |
|
| 22 F |
11 |
Prandtl Meyer flow; gradual compression and expansion; equations of motion |
7.1-3 |
C-22 |
P-06a |
P-05 |
| 23 M |
14 |
Equations of motion; maximum turning angle; reflections |
7.3-7 |
C-23 |
P-06b |
|
| 24 T |
15 |
Buffer day |
|
C-24 |
P-07a |
P-06 |
| R |
17 |
No Class! |
|
|
|
|
| F |
18 |
No Class! |
|
|
|
|
| 25 M |
21 |
Optional review day |
|
C-25 |
|
|
| 26 T |
22 |
Exam II : Applications I & Prandtl Meyer Flow |
|
|
|
|
| 27 R |
24 |
Supersonic oblique shock diffuser |
8.1-2 |
C-27 |
P-07b |
|
| 28 F |
25 |
Supersonic airfoils |
8.5 |
C-28 |
P-08a |
P-07 |
| 29 M |
28 |
Flow with friction, Fanno line flow |
9.1-2 |
C-29 |
P-08b |
|
| 30 T |
29 |
Fanno line flow; nozzles and constant area ducts |
9.2-3 |
C-30 |
P-08c |
|
| 31 R |
31 |
Isothermal flow |
9.4 |
C-31 |
P-08d |
|
| 32 F |
Nov 01 |
Adiabatic flow with friction and area change |
9.5 |
C-32 |
P-09a |
P-08 |
| 33 M |
04 |
Flow with heat transfer; Rayleigh line flow |
10.1-2 |
C-33 |
P-09b |
|
| 34 T |
05 |
Rayleigh line flow |
10.2 |
C-34 |
P-09c |
|
| 35 R |
07 |
Normal shocks; heat addition and area change |
10.3-4 |
C-35 |
P-09d |
|
| 36 F |
08 |
Flow with friction and heat addition |
10.5 |
C-36 |
P-10a |
P-09 |
| 37 M |
11 |
Optional review day |
|
C-38 |
|
|
| 38 T |
12 |
Exam III : Applications II, Fanno & Rayleigh Flow |
|
|
|
|
| 39 R |
14 |
Multidimensional flow; continuity,momentum |
13.1-3 |
C-39 |
P-10b |
|
| 40 F |
15 |
Irrotational flow; velocity potential; course evaluations |
13.4-5 |
C-40 |
|
P-10 |
| TOP |
