Air expands from a storage tank through a converging-diverging nozzle. (See Figure P4.4.) Under certain conditions, it is found that a normal shock exists in the diverging section of the nozzle at an area equal to twice the throat area, with the exit area of the nozzle equal to four times the throat area. Assuming isentropic flow except for the shockwaves, that the air behaves as a perfect gas with constant y = 1.4, and that the storage tank pressure and tem- perature are 200 kPa and 300 K, respectively, determine the following: a) A* for flow from inlet to shock, b) A for flow from shock to exit, c) the mach number at the nozzle exit plane, (d) the stagnation pressure at the nozzle exit plane, e) the exit plane static pressure, and f) the exit plane velocity. T,= 300 K %3D Po= 200 kPa Athroat = 50 cm? Aexit = 4 Atbroạt Akech = 2 Aren

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Hello Sir,Good Evening. I have a question in my homework realated geometry tolerance lesson. The following below is my question. Please advice thank you. "What is the difference between position tolerance and orientation tolerance?"

Statics of Rigid Bodies Note: If you have already answered the problems in this post, kindly ignore it. If not, then answer it. Thank you, Tutor! Content Covered: - Method of Joints Direction: Create two problems based on the topic "Method of Joints" and then solve them with a complete solution. In return, I will give you a good rating. Thank you so much! Note: Please bear in mind to create two problems based on the topic "Method of Joints." Be careful with the calculations in the problem. Kindly double check the solution and answer if there is a deficiency. And also, box the final answer. Thank you so much!