| By the end of this unit, you
should be able to: |
| 1 |
Define quasi 1-D
flow. |
| 2 |
Explain
mathematically and physically the relationship between flow
cross-sectional area and local Mach (or flow speed). |
| 3 |
Explain what we
mean by "choked flow". |
| 4 |
Describe what
happens to the flow inside a Laval nozzle as we change the exit pressure
and / or the reservoir pressure. |
| 5 |
Explain what we
mean by (a) ideally expanded, (b) overexpanded and (c) underexpanded
nozzle. |
| 6 |
Calculate the
flow properties at various locations of an (a) ideally expanded, (b)
overexpanded and (c) underexpanded nozzle. |
| 7 |
Calculate the
location of a shock in a Laval nozzle (assuming there is one). |
| 8 |
Design a
supersonic / hypersonic wind tunnel (i.e. select the appropriate
reservoir, throat and nozzle exit conditions to get the desirable test
section conditions). |
| 9 |
Explain what we
mean by an "unstarted" supersonic wind tunnel. |