Fundamentals-of-Compressible-Fluid-Dynamics Balachandran
CHAPTER 4
6. A conical diffuser of 15 cm has an area
ratio of 4. If the pressure, temperature and velocity at the inlet
section are 0.69 bar, 340 K and 180 m/s, estimate the exit pressure
and exit velocity. What will be the change in impulse
function.
[Ans. p2 = 0.8074 bar; V2 = 45 m/s;
F2 - F1 = 4167.5
N]
7. The Mach number at inlet and exit of a
supersonic diffuser are 3 and 1.5 respectively. The air at inlet
has a pressure of 70 kPa and a temperature of -7°C. If the mass
flow rate of air is 125 kg/s, find (0 stagnation conditions
(ii
) exit area
(iii
) static conditions of air at exit.
[Ans. p0 = 3573.53 kPa; T0
= 745.1 K; Ae = 3.86 x 10-2 m2;
p2 = 700 kPa; T2 = 513.4 K;
V2 = 681.26 m/s] .
8. A nozzle in a wind tunnel gives a test
section Mach number of 3.5. Heated air enters the nozzle from a
large source at 300kPa and 240C. If the mass flow rate through the
test section is 3.5 kg/s, find the pressure, temperature, velocity
and area at the throat and exit sections of the nozzle. Assume the
one-dimensional isentropic flow.
[ANS p1= 4224 kPa; T1=
427.8 K; V1 = - 4I4.6 m/s; A1= 0.245 x I 0^-2m2 ;
pe=10.48 kPa; Te= 148.26 K. Ve=854.25m/s , Ae=
1.6635 x 10^-2m2|
9. Air enters a nozzle having a
throut area of 930 cm2 and attains a Mach number
of 2.5 at the exit. The supply air is at a pressure of
1.05 bar and a temperature of 21"C and is having negligible
velocity find the mass flow rate, area and fluid properties at the
exit of the nozzle.
(Ans. m = 23.02 kg/s; Ar = 0.245 m2; pe =
0.0614 bar. Te= 130.54 K; Ve=
572.55 m/s)
10. A perfectly designed convergent divergent
diffuser is directly fitted to the exit of a duct of uniform
cross-section 0.001 m2. The air at the exit of the duct is at 0.105
MPa and 75°C and is having a velocity of 600 m/s. Estimate the
pressure of air at the exit of the diffuser, if the area of the
diffuser at exit is same as the area at inlet. Also, find the
throat area and the mass flow rate. Assume isentropic flow.
[ Ans. pe =0.3624 MPa; A,= 8 x 10^-4 m2 ; m = 0.6308 kg/s)
PLEASE SOLVE ALL QUESTION BECAUSE TOMORROW IS MY EXAM
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ANS- 6
ANS--10
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandra Chapter 3 7. Air at 3 bar and 300 K enters a duct of varying cross-sectional area of 150m/s. at inlet scetion the area is 0.05 m2. At another section downstream of it, the fluid properties are 2 bar and 280K with a flow velocity of 250m/s, Assuming air to be perfect gas, find the internal thrust produced. H [Ans. -1586.74 N] 8. The entry conditions of air into horizontal duct are 300K 345kPa and 150 m/s the...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 321 Inlet pressure: P1 (kPa) = 588 Inlet Velocity: V1 (m/s) = 97 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 63.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 9 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 1240 K, and its isentropic efficiency is 85%. The...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
UBAV Air flows through a converging-diverging nozzle diffuser. A normal shock stands in the diverging section of the nozzle. Assuming isentropie flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system. Solve wsing equations rather than with the tables Note: The Specific heat ratio and gas constant for air are given as k-1 and R 0.287 kJ/kg-K respectively Give Values Inlet Temperature: TI(K)-340 Inlet pressure: P1 (kPa) - 550 Inlet Velocity:...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. So equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) = 8.81...