![For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question. 1. Air flows adiabatically through a duct. At point 1 the velocity is 240m/s, with T1 - 320 K and p1 170 kPa. Compute i. To ii. (Mach number) ii. At point 2 further downstream V2-290 m/s and P2-135 kPa. What is the stagnation pressure Po2 Hints: Given the properties it is easy to solve for the Mach number using the following formulas To/T =1+0.2M2 Pop (1+0.2M2)2.5 po/p (1+0.2M2)3.5](http://img.homeworklib.com/questions/019aaba0-c724-11ea-9529-7b0de5d6033a.png?x-oss-process=image/resize,w_560)
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For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question....
1)(Hint: Cp=1.005 kJ/kg-K, Cv=0.718 kJ/kg-K, R=0.287 kJ/kg-K). An air-tight room contains 80 kg of air, and...
1)(Hint: Cp=1.005 kJ/kg-K, Cv=0.718 kJ/kg-K, R=0.287 kJ/kg-K). An air-tight room contains 80 kg of air, and a 2-kW baseboard electric resistance heater in the room is turned on and kept on for 15 min. The temperature rise of air at the end of 15 min is 2)An example of when it is appropriate to model a substance as an ideal gas is when a. The pressure and temperature are close to the critcal point b. The pressure and temperature are...
NAME (PRINT): 1. Air (ideal gas with k = 1.4 and Cp = 1.004) enters the...
NAME (PRINT): 1. Air (ideal gas with k = 1.4 and Cp = 1.004) enters the steady-state operating compressor at P1 = 100 kPa and T1 = 17C, compressed adiabatically, and exits at P2 = 330kPa and T2 = 147C. KE and PE can be neglected. Determine (solution process required): a) Isentropic efficiency of the compressor (6 pts) rate of entropy generation per kg of air flow (5 pts).
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging...
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging nozzle with throat area of 1 em and exit area of 2.7 cm2 When the mass flow is 0.05 kg/s, pitot tube reads py 250.6 kPa and 240 kPa at the exit plane. (a) (15 pt.) Is there a normal shock wave in the duct? Justify your answer. If so, compute the Mach number just downstream of the shock (b) (10 pt.) Compute the...
uestion l [use R= 0.287 kJ/kg K, c,-1.0035 kJ/kg K1 a) Air flowing at a rate...
uestion l [use R= 0.287 kJ/kg K, c,-1.0035 kJ/kg K1 a) Air flowing at a rate of 1.6 kg/min is compressed by a 5 kW compressor under steady-state conditions, from 100 kPa and 17°C to 600 kPa and 167°C. During this process, some heat transfer takes place between the compressor and the surrounding medium at 17°C. Determine the rate of entropy change of air during this process, stating clearly any assumptions. (5 Marks)
Analyze a Diesel cycle using a constant specific heat air standard model (cP = 1.004 kJ/kg-K,...
Analyze a Diesel cycle using a constant specific heat air standard model (cP = 1.004 kJ/kg-K, R = 0.287 kJ/kg-K) with the following properties: The temperature and pressure at the beginning of the compression stroke are 300 K and 100 kPa, the compression ratio is 22, and the specific heat addition is 800 kJ/kg. Find the thermal efficiency, cut off ratio, maximum temperature in the cycle, and maximum pressure in the cycle.
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at...
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at a Mach number of 2.5. The pressure and temperature of air are 61.64 kPa and 262.15 K, respectively, upstream of the shock The properties of air are k 1.4 and R = 0.287 kJ/kg K, and the properties of helium arek 1.667 and R 2.0769 kJ/kg-K. [Udara mengalir dengan mantap pada muncung yang mengalami kejutan normal di nombor Mach 2.5. Tekanan dan suhu udara...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandra Chapter 3 7. Air at 3 bar and 300 K enter...
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...
4. (20 points): In a constant-volume the start. The temperature of air at the beginning of the compre temperature attained in the cycle is 2100°C. Take kar-1.4 and Rar = 0.287 kJ/kg K. Determine. a)...
4. (20 points): In a constant-volume the start. The temperature of air at the beginning of the compre temperature attained in the cycle is 2100°C. Take kar-1.4 and Rar = 0.287 kJ/kg K. Determine. a) The compression ratio b) The thermal efficiency of the cycle c) The work done d) The mean effective pressure (MEP) if Pi = 100 kPa Otto cycle the pressure at the end of compression is 12 times thatt ssion is 40°C. The maximum
4. (20...
/6 pts) A quasi-1-D steady adiabatic flow of NEON GAS (R 412 Jkg-K, Cp 1030 J/kg-K & k 53) flows through a gradually contoured channel as shown. Friction is insignificant except for the shock...
/6 pts) A quasi-1-D steady adiabatic flow of NEON GAS (R 412 Jkg-K, Cp 1030 J/kg-K & k 53) flows through a gradually contoured channel as shown. Friction is insignificant except for the shock. The mass flowrate is 70.2 kg/s State properties are only partially known. The flow velocity just after the normal shock is A12mis at section "Y. A) Find the stagnation temperature. T。= K and the critical temperature. T., K B) Find the flow Mach number just before...
need help with letter j,k,l,m,n,o just those i solved the top ones just the last 6...
need help with letter j,k,l,m,n,o just those i solved the top
ones just the last 6 thanjs you
mine the temperature (K) at the throat. Your Answer=289.711 Correct! Exact Answer=289.71 +/- 1.0E+00 e) Determine the velocity (m/s) at the throat. Your Answer 341.18 Correct! Exact Answer 341.183 +/- 1.3E+00 f) Determine the pressure (kPa) at the throat. Your Answer=314.09 Correct! Exact Answer=314.10 +/- 1.2E+00 g) Determine the mass flow rate (kg/s) through the nozzle Your Answer=1.0826 Correct! Exact Answer= 1.08264...
NAME (PRINT): 1. Air (ideal gas with k = 1.4 and Cp = 1.004) enters the steady-state operating compressor at P1 = 100 kPa and T1 = 17C, compressed adiabatically, and exits at P2 = 330kPa and T2 = 147C. KE and PE can be neglected. Determine (solution process required): a) Isentropic efficiency of the compressor (6 pts) rate of entropy generation per kg of air flow (5 pts).
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging nozzle with throat area of 1 em and exit area of 2.7 cm2 When the mass flow is 0.05 kg/s, pitot tube reads py 250.6 kPa and 240 kPa at the exit plane. (a) (15 pt.) Is there a normal shock wave in the duct? Justify your answer. If so, compute the Mach number just downstream of the shock (b) (10 pt.) Compute the...
uestion l [use R= 0.287 kJ/kg K, c,-1.0035 kJ/kg K1 a) Air flowing at a rate of 1.6 kg/min is compressed by a 5 kW compressor under steady-state conditions, from 100 kPa and 17°C to 600 kPa and 167°C. During this process, some heat transfer takes place between the compressor and the surrounding medium at 17°C. Determine the rate of entropy change of air during this process, stating clearly any assumptions. (5 Marks)
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at a Mach number of 2.5. The pressure and temperature of air are 61.64 kPa and 262.15 K, respectively, upstream of the shock The properties of air are k 1.4 and R = 0.287 kJ/kg K, and the properties of helium arek 1.667 and R 2.0769 kJ/kg-K. [Udara mengalir dengan mantap pada muncung yang mengalami kejutan normal di nombor Mach 2.5. Tekanan dan suhu udara...
4. (20 points): In a constant-volume the start. The temperature of air at the beginning of the compre temperature attained in the cycle is 2100°C. Take kar-1.4 and Rar = 0.287 kJ/kg K. Determine. a) The compression ratio b) The thermal efficiency of the cycle c) The work done d) The mean effective pressure (MEP) if Pi = 100 kPa Otto cycle the pressure at the end of compression is 12 times thatt ssion is 40°C. The maximum
4. (20...
/6 pts) A quasi-1-D steady adiabatic flow of NEON GAS (R 412 Jkg-K, Cp 1030 J/kg-K & k 53) flows through a gradually contoured channel as shown. Friction is insignificant except for the shock. The mass flowrate is 70.2 kg/s State properties are only partially known. The flow velocity just after the normal shock is A12mis at section "Y. A) Find the stagnation temperature. T。= K and the critical temperature. T., K B) Find the flow Mach number just before...
need help with letter j,k,l,m,n,o just those i solved the top
ones just the last 6 thanjs you
mine the temperature (K) at the throat. Your Answer=289.711 Correct! Exact Answer=289.71 +/- 1.0E+00 e) Determine the velocity (m/s) at the throat. Your Answer 341.18 Correct! Exact Answer 341.183 +/- 1.3E+00 f) Determine the pressure (kPa) at the throat. Your Answer=314.09 Correct! Exact Answer=314.10 +/- 1.2E+00 g) Determine the mass flow rate (kg/s) through the nozzle Your Answer=1.0826 Correct! Exact Answer= 1.08264...
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