Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
6th Edition
ISBN: 9781259683268
Author: Anderson, John
Publisher: Mcgraw-hill Higher Education (us)
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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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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
A flow is isentropically expanded to supersonic speeds in aconvergent-divergent nozzle. The reservoir and exit pressures are 1 and0.3143 atm, respectively. What is the value of Ae/A∗?
A 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.
Chapter 10 Solutions
Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
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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- Consider 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_forwardCarbon 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?arrow_forward56. 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_forward
- D5. 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_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_forwardQ2) 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_forward
- A convergent-divergent operating isentropically. Pback P01 = 0.8 3 nozzle has an exit Mach number of 1.8 when If the back pressure is increased such that: Show Transcribed Text a shock appears in the divergent portion. What is Aerit Ashockarrow_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_forward
- 21) Prove that for isentropic flow of perfect gas the effects of an area change on the flow properties (P,V,T,p) are opposite for subsonic and supersonic flow.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_forwardThe stagnation chamber of a wind tunnel is connected to a high pressure air bottle farm which is outside the laboratory building. The two are connected by a long pipe which has a inside diameter of 4 inches. If the static pressure ratio between the bottle farm and the stagnation chamber is 10 and the bottle farm static pressure is 100 atm, how long can the pipe be without choking and what is the change in entropy? Assume adiabatic,subsonic, one-dimensional flow with a friction coefficient of 0.005.arrow_forward
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