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Solution
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Across
1
Inlet flow adjusts to demand.
3
Simple ducting
5
Opposite of Convergent
7
Aerodynamic forcing causes cycle stresses
8
For Compressor station 3-3R
9
How compressors work equation
10
Low airflow
12
Pressure difference between suction and pressure sides of the blades and stators
17
Difficult achieving efficient, stable supersonic diffusion over a wide mach range
19
Accounts for the boundary layer; uses nozzle geo. to predict losses instead of using pi_n
20
Accounts for thrust loss due to non-axial flow out of the nozzle.
21
Self-induced vibration that occurs if a flow-induced forcing function.
Down
2
Installation loss at inlet
4
To bring air required by the engine from free stream.
6
M_max = 1 at exit for nozzle
11
Momentum loss due tp wall friction in the nozzle.
13
What all the parts we learned make :)
14
Yourself
15
Coefficient of ratio of the 1-D area from cycle calculation for the nozzle throat
16
Work as much as the compressor needs
18
Between compressor stations 1-2R