Q5: A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is Poand exhausts to the atmosphere with a pressure of Po. The area A at distance x from the throat is given by (A = At (1 + 0.75x/L)), where At is the throat cross- sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio PoJPb, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio P/Po- Ans.: 0.45 L = 0.753 Р.

Q5: A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is Poand exhausts to the atmosphere with a pressure of Po. The area A at distance x from the throat is given by (A = At (1 + 0.75x/L)), where At is the throat cross- sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio PoJPb, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio P/Po- Ans.: 0.45 L = 0.753 Р.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Q3- A isentropic nozzle is supplied with air from large reservoir, where the T-1000 °C and P=10 bars. a- Calculate P, T and V at nozzle exit if M₂=2. c) What is the maximum velocity?
I need the answer as soon as possible
i need the answer quickly
Need proper answer with details explanation
i need the answer quickly
Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of V235 m/s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, C, = 917 J/Kg.k and R = 260 J/Kg.k) air at 30 C tank conditions Pan= 101 LPa
If a liquid enters a pipe of diameter d with a velocity, v. what will irs velocity at the exit be if the diameter reduces to 0.5d?
A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi lled no more thanone-third with liquid, which, at room temperature, maintainsthe gaseous phase at about 850 psia. (a) If a valve isopened that simulates a converging nozzle with an exitdiameter of 0.050 in, what mass fl ow and exit velocityresults? (b) Repeat the calculations for helium.
Q1: A converging-diverging frictionless nozzle is used to accelerate an airstream emanating from a large chamber. The nozzle has an exit area of 30cm² and a throat area of 15cm². If the chamber temperature is 500K, and the back pressure is 101kPa, calculate the following: a. Minimunt chamber pressure (po) to choke the nozzle. b. Mass flow rate for a chamber pressure (po) of 400kPa. c. Mass flow rate for a chamber pressure (po) of 105kPa.
(WEB) Air at 17°C, 100 kPa flows in a duct. A stagna- P4-46 tion tube connected to a U-tube manometer filled with mercury is placed in the duct. Using data on the figure, find the air velocity Assume atmospheric pressure is 100 kPa Air at 17°C, 100 kPa 30 mm Mercury
Consider a liquid jet which is coming out from a small hole areaof cross section S with velicity q1 and making an angle A with the horizon. Find the velocity of the liquid at point 2?
Q2) Air expand from storage tank through a convergent-divergent nozzle as in figure. Under certain condition it is found that a normal shock wave 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 fourth times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with constant (y-1.4), and that the storage tank pressure and temperature are 200kpa, and 300K, determine the following. a) Critical area for flow from inlet to shock. b) Critical area for flow from shock to exit. c) Mach number at nozzle exit plane. d) Stagnation pressure at nozzle exit plane. e) Exit plane static pressure. f) Exit plane velocity. T. = 300 K Po = 200 kPa Athroat = 50 cm² Aexit = 4 Ahroat Ashock = 2 Athroor