an argon (cp= 0.518 Lk/kg.K, and k= 1.67) has a velocity V=750 m/s, pressure P= 120...
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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 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 co=0.518KJ/Kg. K=1.67 has a velocity 750m/s pressure=120kpa and T=175c if the argon is at...
An argon co=0.518KJ/Kg. K=1.67 has a velocity 750m/s pressure=120kpa and T=175c if the argon is at stagnation state,calculate pressure (p0) and temperatureT0)
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)
/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...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combust...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combustion chamber as 843.5 kPa and the temperature at the turbine exit to be 518 K, determine the velocity of the exhaust gases. Give your answer in m/s to 2 decimal places. Assume ideal operation for all components and constant specific...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at...
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at the inlet state to M -1.3 at the outlet, where local isentropic stagnation conditions are known to be 385 kPa and 350 K. Compute the local isentropic stagnation pressure and temperature at the inlet and the static pressure and temperature at the duct outlet. Flow Inlet Outlet
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...
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...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at the inlet state to M -1.3 at the outlet, where local isentropic stagnation conditions are known to be 385 kPa and 350 K. Compute the local isentropic stagnation pressure and temperature at the inlet and the static pressure and temperature at the duct outlet. Flow Inlet Outlet
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