Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 10, Problem 10.2P
A flow is isentropically expanded to supersonic speeds in convergent-divergent nozzle. The reservoir and exit pressures arc 1 and 0.3 143 atm, respectively. What is the value of
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2. 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 cm?. If the exit area is 13 cm? calculate:
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?
b. Air flows in a converging-diverging nozzle
from stagnation conditions at P, = 500 kPa
and T. = 400 K as shown in Fig.2. The exit
Throat
To
static pressure is 450 kPa, and the throat
ME
Po
and exit areas are 0.01 m? and 0.015 m2
Po
respectively. Assuming isentropic flow,
Supersonie
nozzle
Ag
determine the Mach number, ME at exit
and the mass flow rate th when the flow is
supersonic in the divergence section of the
PE
(Ma, = 1)
duct.
(Take for air, K=1.4, and R= 287 m?/s?.K)
Fiq.2
Carbon dioxide (k=1.289; Cp=0.846 kj/kgK; R=0.1889 kj/kgk) enters a convergent-divergent nozzle at 65 m/s, 350 oC and 300 kPa and leaves the nozzle in a supersonicleaves at speed. What is the pressure of carbon dioxide in the neck of the nozzle?
Chapter 10 Solutions
Fundamentals of Aerodynamics
Ch. 10 - The reservoir pressure and temperature for a...Ch. 10 - A flow is isentropically expanded to supersonic...Ch. 10 - A Pitot tube inserted at the exit of a supersonic...Ch. 10 - For the nozzle flow given in Problem 10.1, the...Ch. 10 - A closed-form expression for the mass flow through...Ch. 10 - Prob. 10.6PCh. 10 - A convergent-divergent nozzle with an...Ch. 10 - For the flow in Problem 10.7, calculate the mass...Ch. 10 - Consider a convergent-divergent nozzle with an...Ch. 10 - A 20 half-angle wedge is mounted at 0 angle of...
Ch. 10 - The nozzle of a supersonic wind tunnel has an...Ch. 10 - We wish to design a supersonic wind tunnel that...Ch. 10 - Consider a rocket engine burning hydrogen and...Ch. 10 - For supersonic and hypersonic wind tunnels, a...Ch. 10 - Return to Problem 9.18. where the average Mach...Ch. 10 - Return to Problem 9.19, where the average Mach...Ch. 10 - A horizontal flow initially at Mach I flows over a...Ch. 10 - Consider a centered expansion wave where M1=1.0...
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- Fast please.arrow_forwardA nozzle is said to be choked when... oblique shock waves occur. oblique expansion waves occur. the Mach number in the throat is one. the maximum flow rate has been attained. normal shock occurs.arrow_forwardConsider the isentropic supersonic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 10.25. The reservoir pressure and temperature are 5 atm and 600◦R, respectively. Calculate M, p, and T at the nozzle exit.arrow_forward
- 56. A supersonic aircraft flies with a velocity greater by 39 m-s1 at 7600 m elevation, (T = - 51 C° at 7600 m) and (T =- 55 C° at 8600 m, M = 1.9), determine the ratio of Mach no.s.arrow_forwardD5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic flow at the outlet with no shacks inside the nozzle. Determine the mach number and static pressure at the outlet if the area of the outlet is 0.900 m2, the area of the throat is 0.490m2, and the stagnation pressure is 215 kPa.arrow_forwardTurbomachines 4arrow_forward
- Q2) Air (Y=1.4 and R=287 J/kg.k) flow through a converging - diverging nozzle designed to operate isentropically with supersonic flow at exit. The inlet and throat diameters of the nozzle are 43 mm and 25 mm respectively. The inlet pressure and temperature are 86 kpa and 298 k respectively and the back pressure (pressure at the exit section of the nozzle) is 12 kpa. What should be the exit diameter of the nozzle which corresponds to the maximum obtainable value of the Mach number? What are the mass flow rate of the air and its exit temperature. Find also the range of back pressure over which the nozzle is chocked.arrow_forward2. = Air enters a constant-area duct at Mach 3 and stagnation conditions 750 K and 1.3 MPa. Assume y 1.4. In the duct it undergoes frictionless heating such that the exit Mach number is unity. Consider two cases: (a) normal shock at the inlet of the duct and (b) shock-free supersonic heating. Determine the stagnation temperature and pressure at the exit in each case. Is there any reason why the total energy transfer should differ (or be equal) in the two cases?arrow_forwardQ1) Air is to be expanded to Mach number (2.0) in a convergent-divergent nozzle from an inlet velocity of (100 m/s). The inlet area is (50cm³). Inlet static temperature is (500K) and static pressure is 101.3 kpa. Assuming isentropic flow determine: 1. The Mach number at the inlet. 2. The stagnation pressure and temperature. 3. The temperature and pressure at the throat. 4. The velocity and temperature at exit. 5. The throat and exit temperature. 6. The mass flow rate.arrow_forward
- (1) The velocity of supersonic flow at exit section of a nozzle, when Ae/A* = 2.4, To = 137 oC is, * 665.4 m-s-1 1438.4 m-s-1 100.9 m-s-1 O 102.1 m-s-1arrow_forwardAsap.. An isentropic flow through a convergent-divergent nozzle with an exit-to-throat ratio of Ae/At = 2.2. The flow through the throat is subsonic and the exit pressure is pe = 0.967 atm. The inlet pressure is p = 1 atm. Determine the Mach number (Mt) at the Throat.arrow_forwardQ6- Air flows isentropically through converging-diverging nozzle. At a section where nozzle area is 0.0012 m², the local pressure, temperature and Mach number are 4.1 bars, 4.4 °C and 0.52 respectively. The back pressure is 2.06 bar. The Mach number at the throat, the mass flow rate, and the throat area are to be determined.arrow_forward
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