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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 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).
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 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 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...
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...
A gas in a cylinder piston system occupies V, - 15 mºat P. = 220 kPa and T, -20°C. Then, the gas undergoes a polytropic compression process until its temperature becomes T, 300'C. The entropy change of the gas during this process is AS - -1.7626 kJ/K, (AS-S.-5.). By assuming ideal gas (R = 0.3 kJ/kg.K. cp = 0.8 kJ/kg.K. cv = 0.5 kJ/kg.K), determine: 3pt) the mass of the gas, m (kg) = (9pt) the work transfer, W (kl)...
A system with 0.15 moles of Argon gas (Ar) has a total thermal energy of 5.4-kJ and a volume of 0.3m3. What is the temperature and pressure of the gas? P=12-kPa T=2900-K