gas dynamics of variable area ducts
DESCRIPTION
Gas Dynamics of Variable Area Ducts. P M V Subbarao Professor Mechanical Engineering Department I I T Delhi. Development of Efficient and Compact Passive Devices…. System of Equaions. Combine conservation, state equations– can algebraically show. - PowerPoint PPT PresentationTRANSCRIPT
Gas Dynamics of Variable Area Ducts
P M V Subbarao
Professor
Mechanical Engineering Department
I I T Delhi
Development of Efficient and Compact Passive Devices….
0A
dA
V
dV
ρ
dρ
0V
dVM
2p
dp
D
fdxM
2 2
22
h
2 γγ
0
V
dV
2
M1
T
dT
TC
q2
22
p
'''
γδ
0T
dT
ρ
dρ
p
dp
0V
dV
M
dM
T
dT2
2
2
2
System of Equaions
Combine conservation, state equations– can algebraically show
2
0p
'''
h
22
2
2
2
M1TC
q
A
dA2
D
fdxM
M1
M2
11
M
dMγ
δγ
γ
So we have three ways to change Mach number of a flow
– area change (dA):
– friction: f > 0, same effect as –dA
– heat transfer: heating, q’’’ > 0, like –dA cooling, q’’’ < 0, like +dA
Effect of Shape of duct on Flow
2
0p
'''
h
22
2
2
2
M1TC
q
A
dA2
D
fdxM
M1
M2
11
M
dMγ
δγ
γ
Pure shape effects :
A
dA2
M1
M2
11
M
dM2
2
2
2γ
A
dA
1M
M12
M
dM2
2
2
2 γ
A
dA
1M2
M12
M
dM2
2γ
1M2
M12M
dM
A
dA
2
2
γ
Pure Shape Effects …..
p
dp1
u
duM2
γ
p
dp1
A
dA
M1
M2
2
γ
ρ
dρ
p
dpγ
Subsonic Nozzle Subsonic Diffuser
dA < 0 & M <1So, du > 0 & dp <0
dA > 0 & M <1So, du < 0 & dp>0
A
dA
1M
1
u
du2
T
dT
A
dA
M1
M12
2
γ
Supersonic Diffuser Supersonic Nozzle
dA < 0 & M >1So, du < 0 & dp >0
dA > 0 & M >1So, du >0 & dp<0
p
dp1
u
duM2
γ
p
dp1
A
dA
1M
M2
2
γ
A
dA
1M
1
u
du2
ρ
dρ
p
dpγ
ρ
dρ
A
dA
1M
M2
2
T
dT
A
dA
1M
M12
2
γ
Generation of High Pressure from Supersonic velocity
p
dpM
u
du 2
γ
p
dp1
M
M1
A
dA2
2
γ
p
dp1
ρ
dρ
γ
p
dp1
T
dT
γ
γ
A
dA
1M
1
u
du2
Generation of Supersonic Velocity from Rest
p
dpM
u
du 2
γ
p
dp1
M
M1
A
dA2
2
γ
p
dp1
ρ
dρ
γ
p
dp1
T
dT
γ
γ Rocket Nozzle
X – 15 : Hypersonic Research at the Edge of Space
The X-15 was air launched from a B-52 aircraft at about 45,000 ft and speeds upward of 500 mph. The airplane first set speed records in the Mach 4-6 range with Mach 4.43 on March 7, 1961; Mach 5.27 on June 23, 1961; Mach 6.04 on November 9, 1961; and Mach 6.7 on October 3, 1967. It also set an altitude record of 354,200 feet (67 miles) on August 22, 1963, and provided an enormous wealth of data on hypersonic air flow.Aerodynamic heating, control and stability at hypersonic speeds, reaction controls for flight above the atmosphere, piloting techniques for reentry, human factors, and flight instrumentation.
Intake at Design Altitude
p1
p2pthroat
p
p2
p*
p1
0p
dp1
M
M1
A
dA2
2
γAt M=1
Minimum Area = A* : Also called throat
*** AcρρuA
u
RT
ρ
ρ
u
c
ρ
ρ
A
A **
γ
Frictional Adiabatic Flow in A Variable Area Duct
2
0p
'''
h
22
2
2
2
M1TC
q
A
dA2
D
fdxM
M1
M2
11
M
dMγ
δγ
γ0
A
dA2
D
fdxM
M1
M2
11
M
dM
h
22
2
2
2
γ
γ
Constant Mach number frictional flow
h
2
2D
fMA
dx
dA γ