An argon co=0.518KJ/Kg. K=1.67 has a velocity 750m/s pressure=120kpa and T=175c if the argon is at...
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argon co=0.518KJ/Kg. K=1.67 has a velocity 750m/s pressure=120kpa
and T=175c if the argon is at...
An argon (Cp= 0.518 KJ/kg.k, and K= 1.67) has velocity V =750m/s, pressure P = 120...
An argon (Cp= 0.518 KJ/kg.k, and K= 1.67) has velocity V =750m/s, pressure P = 120 kPa, and temperature T = 175 C. If the argon is at stagnation state, calculate the pressure (P0) and temperature (T0).
An argon (Cp = 0.518 KJ/kg. K, and K=1.67) has velocity V = 750 m/s, pressure P =120 kPa
An argon (Cp = 0.518 KJ/kg. K, and K=1.67) has velocity V = 750 m/s, pressure P =120 kPa, and temperature T = 175 °C. If the argon is at stagnation state, calculate the pressure (P0) and temperature (T0).
an argon (cp= 0.518 Lk/kg.K, and k= 1.67) has a velocity V=750 m/s, pressure P= 120...
an argon (cp= 0.518 Lk/kg.K, and k= 1.67) has a velocity V=750 m/s, pressure P= 120 kpa and tempreture 175 c. if argon is at stagnation state, calculate the pressure (p0) and temreture (T0).
Question # 3 (35pts) 50kg/s of air steadily enter a diffuser at a velocity of 750m/s...
Question # 3 (35pts) 50kg/s of air steadily enter a diffuser at a velocity of 750m/s and a static pressure of 20kPa. The air leaves the diffuser at a velocity of 90m/s and a static pressure of 330kPa. The entrance area of the diffuser is 0.25m², and its exit area is 0.28m². Determine the magnitude and direction of the force on the strut that holds the diffuser stationary assuming that this diffuser is operated in an atmospheric pressure po =...
Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and 300 kPa, and it...
Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and 300 kPa, and it leaves the nozzle at a supersonic velocity. The throat diameter is 3 cm. For Argon R= 208.1 Pa.m3/kg.K; k= 1.667. Determine (a) the stagnation temperature and pressure (8 points) (b) the critical temperature and pressure at the throat (7 points) (c) the velocity at the throat (4 points) (d) the mass flow rate. (6 points)
solve all parts please Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and...
solve all parts please
Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and 300 kPa, and it leaves the nozzle at a supersonic velocity. The throat diameter is 3 cm. For Argon R= 208.1 Pa.mº/kg.K; k= 1.667. Determine (a) the stagnation temperature and pressure (8 points) (b) the critical temperature and pressure at the throat (7 points) (c) the velocity at the throat (4 points) (d) the mass flow rate. (6 points)
Argon enters an insulated nozzle at 280 kPa, 1300 K, 10 m/s and exits at 645...
Argon enters an insulated nozzle at 280 kPa, 1300 K, 10 m/s and exits at 645 m/s. Assume argon is an ideal gas and has a constant specific heat. Determine a) The exit temperature of the argon under the actual process (K). b) The ideal exit temperature of the argon (K) under the isentropic process if the isentropic efficiency of the nozzle is 90 percent. c) The exit pressure of the argon (kPa). d) The amount of specific entropy generation...
/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...
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question....
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...
mass flow rate 15 kh/s DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013...
mass flow rate 15 kh/s
DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013 kPa Inlet Stagnation Temperature 1200 K Mean Blade Diameter 25 cm Rotor Speed 26,500 rpm Fou usbine Axial Velocity- 180 m/s inlet to Rotor Angle, α= 700 Exit Rotor Angle as 0 Assuming variable specific heats and the axial velocity remains constant; (a) Construct the velocity diagrams for the stage (b) Calculate work, Aw (c) The power developed based on the mean blade diameter,...
Question # 3 (35pts) 50kg/s of air steadily enter a diffuser at a velocity of 750m/s and a static pressure of 20kPa. The air leaves the diffuser at a velocity of 90m/s and a static pressure of 330kPa. The entrance area of the diffuser is 0.25m², and its exit area is 0.28m². Determine the magnitude and direction of the force on the strut that holds the diffuser stationary assuming that this diffuser is operated in an atmospheric pressure po =...
Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and 300 kPa, and it leaves the nozzle at a supersonic velocity. The throat diameter is 3 cm. For Argon R= 208.1 Pa.m3/kg.K; k= 1.667. Determine (a) the stagnation temperature and pressure (8 points) (b) the critical temperature and pressure at the throat (7 points) (c) the velocity at the throat (4 points) (d) the mass flow rate. (6 points)
solve all parts please
Argon gas enters a converging-diverging nozzle at 60 m/s, 310 °C, and 300 kPa, and it leaves the nozzle at a supersonic velocity. The throat diameter is 3 cm. For Argon R= 208.1 Pa.mº/kg.K; k= 1.667. Determine (a) the stagnation temperature and pressure (8 points) (b) the critical temperature and pressure at the throat (7 points) (c) the velocity at the throat (4 points) (d) the mass flow rate. (6 points)
/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...
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...
mass flow rate 15 kh/s
DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013 kPa Inlet Stagnation Temperature 1200 K Mean Blade Diameter 25 cm Rotor Speed 26,500 rpm Fou usbine Axial Velocity- 180 m/s inlet to Rotor Angle, α= 700 Exit Rotor Angle as 0 Assuming variable specific heats and the axial velocity remains constant; (a) Construct the velocity diagrams for the stage (b) Calculate work, Aw (c) The power developed based on the mean blade diameter,...
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