Download - Gas Dynamics ESA 341 Chapter 3
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Gas DynamicsESA 341Chapter 3
Dr Kamarul Arifin B. Ahmad
PPK Aeroangkasa
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Normal shock waves
Definition of shock wave Formation of normal shock wave Governing equations Shock in the nozzle
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Definition of shock waveShock wave is a very thin region in a flow where a supersonic flow is decelerated to subsonic flow. The process is adiabatic but non-isentropic.
Shock wave
V
P
T
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Formation of Shock WaveA piston in a tube is given a small constant velocity increment to the right magnitude dV, a sound wave travel ahead of the piston.
A second increment of velocity dV causing a second wave to move into the compressed gas behind the first wave.
As the second wave move into a gas that is already moving (into a compressed gas having a slightly elevated temperature), the second waves travels with a greater velocity.
The wave next to the piston tend to overtake those father down the tube. As time passes, the compression wave steepens.
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Types of Shock Waves:
Normal shock wave - easiest to analyze
Oblique shock wave - will be analyzed based on normal shock relations
Curved shock wave - difficult & will not be analyzed in this class
- The flow across a shock wave is adiabatic but not isentropic (because it is irreversible). So:
0201
0201
PP
TT
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Governing Equations
1
1
1
1
T
P
V
2
2
2
2
T
P
VConservation of mass:
Conservation of momentum:
Rearranging:
Combining:
AVAV 2211
122221
121121
1221
VVVPP
VVVPP
VVmAPP
2
2121
22
1
212121
PP
VVV
PPVVV
21
22
2121
11VVPP
Conservation of energy:
Change of variable:
0
22
2
21
1 22Tc
VTc
VTc ppp
2
2
1
121
22 1
2
PP
VV
combine
22
2
221
1
1
1
2
1
2V
PV
P
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Continued:
Multiplied by 2/p1:
Rearranging:
2
2
1
1
2121 1
211
PP
PP
1
2
1
2
1
2
1
2
1
211
P
P
P
P
1
2
1
2
1
2
11
111
P
P
1
2
1
2
1
2
11
111
PP
PP
or
Governing Equations cont.
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1
2
1
2
2
1
1
2
11
111
PP
PP
V
V
2
1
1
2
1
2
P
P
T
T
2
1
1
2
1
2
11
11
PP
PP
T
T
Governing Equations cont.
From conservation of mass:
From equation of state:
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Governing Equations cont.
2211 VV
222
211
2
2222
2111
1221
11 MPMP
Pa
VPVP
VVmAPP
22
21
1
2
22
2
21
1
21
1
21
1
22
M
M
T
T
Vh
Vh
C
O
M
BINE
Conservation of mass
Conservation of momentum
Conservation of energy
02
21
1
)2
11(
1
)2
11(
2
11
12
11
1
21
22
21
22
21
22
41
42
222
22
22
221
21
21
222
2
2212
1
1
222
211
1
1
2211
MM
MMMMMM
M
MM
M
MM
MM
MM
M
M
RTMRT
PRTM
RT
P
VV
Expanding the equations
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Governing Equations cont.
12
212
1
21
2
M
MM
Solution:
Mach number cannot be negative. So, only the positive value is realistic.
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Governing Equations cont.
1
1
1
2
1
1
121
11
22
11
21
1
21
1
21
1
2
22
21
1
2
21
2
21
21
1
2
22
21
1
2
M
P
P
M
M
P
P
M
MM
T
T
M
M
T
T
2)1(
)1(
121
11
22
11
1221
21
21
1
2
21
2
21
21
21
21
1
1
2
2
1
2
1
2
1
1
2
M
M
M
MM
MM
M
T
T
M
M
V
V
Temp. ratio
Pres. ratio
Dens. ratio
Simplifying:
1
2
3
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Stagnation pressures:
Other relations:
1
12
21
1
21
1 21
1
21
22
01
02
1
2
01
1
2
02
01
02
M
M
M
P
P
P
P
P
P
P
P
P
P
2
02
02
01
2
01
1
01
01
02
1
02
P
P
P
P
P
P
P
P
P
P
P
P
Governing Equations cont.
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Entropy change:
But, S02=S2 and S01=S1 because the flow is all isentropic before and after shockwave.
So, when applied to stagnation points:
But, flow across the shock wave is adiabatic & non-isentropic:
And the stagnation entropy is equal to the static entropy:
So:
Shock wave
1 2
1
2
1
212 lnln
P
PR
T
Tcss p
01
02
01
020102 lnln
P
PR
T
Tcss p
0201 TT
1ln 1201
020102
ss
P
PRss
1exp 12
01
02
R
ss
P
P Total pressure decreases across shock wave !
Governing Equations cont.
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Group Exercises 3
1. Consider a normal shock wave in air where the upstream flow properties are u1=680m/s, T1=288K, and p1=1 atm. Calculate the velocity, temperature, and pressure downstream of the shock.
2. A stream of air travelling at 500 m/s with a static pressure of 75 kPa and a static temperature of 150C undergoes a normal shock wave. Determine the static temperature, pressure and the stagnation pressure, temperature and the air velocity after the shock wave.
3. Air has a temperature and pressure of 3000K and 2 bars absolute respectively. It is flowing with a velocity of 868m/s and enters a normal shock. Determine the density before and after the shock.
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0sM
11 M 12 M
01
01
1
1
1
T
P
T
P
0102
0102
12
12
12
TT
PP
TT
PP
1M 2M1
2
P
P
1
2
T
T
1
2
1
2
a
a
01
02
P
P
1
02
P
P
Stationary Normal Shock Wave Table – Appendix C: