Engineering, 18.02.2021 23:40 sailormaries7101
Air flow isentropically through a supersonic convergent divergent nozzle with 0.5 kg/s. At the inlet, the pressure is 680 kPa and the temperature is 295 K, and the area is 6.5 cm2. If the exit area is 13 cm2 calculate: (1 point) a- The stagnation pressure and temperature. b- The exit Mach number. c- The exit pressure and temperature. d- The area and velocity at the throat. e- What will be the corresponding exit Mach number if the flow completely subsonic in the nozzle
Answers: 1
Another question on Engineering
Engineering, 03.07.2019 15:10
Apiston-cylinder with a volume of 0.25 m3 holds 1 kg of air (r 0.287 k/kgk) at a temperature of 100 c. heat transfer to the cylinder causes an isothermal expansion of the piston until the volume triples. how much heat is added to the piston-cylinder?
Answers: 3
Engineering, 04.07.2019 18:10
Steel is coated with a thin layer of ceramic to protect against corrosion. what do you expect to happen to the coating when the temperature of the steel is increased significantly? explain.
Answers: 1
Engineering, 04.07.2019 18:10
If a particle moves along a path such that r : (3 sin t) m and ? : 2t rad, where t is in seconds. what is the particle's acceleration in m/s in 4 seconds? a)- 16.43 b)- 16.29 c)- 15.21 d)- 13.79
Answers: 1
Engineering, 04.07.2019 18:10
Afluid flows with a velocity field given by v=(x/t)i.. determine the local and convective accelerations when x=3 and t=1.
Answers: 2
You know the right answer?
Air flow isentropically through a supersonic convergent divergent nozzle with 0.5 kg/s. At the inlet...
Questions
Mathematics, 25.03.2020 05:03
Mathematics, 25.03.2020 05:03
Mathematics, 25.03.2020 05:03
Biology, 25.03.2020 05:03
Biology, 25.03.2020 05:03
Mathematics, 25.03.2020 05:03
