48. Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. (a) Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure, temperature, linear velocity, density, and mass velocity? (b) What are the values of p*, T", u*, and G* corresponding to reservoir conditions? (c) Assuming the nozzle is to be used supersonically, what is the maximum Mach number at the discharge of the divergent section? For air y= 1.4 and M = 29. *

48. Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. (a) Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure, temperature, linear velocity, density, and mass velocity? (b) What are the values of p, T", u, and G* corresponding to reservoir conditions? (c) Assuming the nozzle is to be used supersonically, what is the maximum Mach number at the discharge of the divergent section? For air y= 1.4 and M = 29. *

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

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Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? Write your answers according to order of properties asked. *
For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.
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1.AB
For given air flow with Mach number in test section (i.e. at CD nozzle exit), Me = 8, T01 = 300 K, pressure in test section = 4000 Pa. (1) What is the value of static temperature, stagnation temperature and stagnation pressure in the test section? (2) What is the value of stagnation pressure in the storage thank? (3) What do you conclude about state of air? (4) What is the solution to rectify this problem. i.e. (5)What is the minimum temperature of air should you take in reservoir tank? At this condition, what is mass flow rate in test section? Low pressure air chamber High pressure air storage Storage tank T01 = 300K P01 = ? Settling chamber Pressure regulator Nozzle Screens Test-section Pe = 4000 Pa Me = 8 Te = ? K Sonic throat P0e =? T0e = ? Blow down wind Tunnel (Open circuit type) Diffuser Second throat vacuum tank
Q2: Air (y = 1.4) enters a converging-diverging diffuser with a Mach number of 2.8, static pressure pi of 100 kPa, and a static temperature of 20°C. For the flow situation shown in Figure, find the exit velocity, exit static pressure, and exit stagnation pressure. Ans: Ve = 55.093 m/s; Pe = 2236.678 kPa; Poe = 2252.44 kPa i M₁ = 2.8 A₁ = 0.10 m² A₂ = 0.50 m² A₁ = 0.25 m²
Parvinbhai
Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75. a. What are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? b. What are the values of p*(in atm), T*(in K), u*(in m/s), and G* (in kg/m2.s) corresponding to reservoir conditions?
Air flows isentropically through a duct as shown in the figure below. For the conditions shown, find the Mach number at both stations 1 and 2 and the flowrate. The diameter is not necessarily constant. Ma₁ (1) D₁ = 0.15 m V₁ = 40 m/s P1 = 4 atm abs. Ma₁ = Ma₂ = i m₁ = M. kg/s Ma₂ (2 T₂ = 225 K P2 = 2 atm abs.
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-.2. A perfect gas (y = 1.4) enters a converging-diverging nozzle with a Mach number of 0.50 and local pressure and temperature values of 280 kPa and 280 K, respectively. The nozzle throat area is 6.5 X 10-4 m? and the nozzle exit area is 26 X 10-4 m². The nozzle exit pressure is 170 kPa. (a) What are the values of the Mach number and the stream temperature at the exit? (b) At what area does the shock occur? Show your method of solution on a skeleton flow chart.
Q6: Air following through constant area duct encounters stationary shock as shown in figure. Find the Mach number, temperature, pressure, stagnation pressure, stagnation temperature and velocity after the shock. Ans.: M2 = 0.6746, T2 = 344 K, p2 = 137 kPa, To = 375 K, po = 186 kPa. V1=500 m/s P;=50 kPa 1-250 K → (1) | (2)