Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 10, Problem 10.4P
For the nozzle flow given in Problem 10.1, the throat area is
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5. A wind tunnel consists of an entry contraction, a constant-area working section of area
0.5 m?, a diffuser and a fan of area 1 m?, as shown in Fig. 2. The air is pulled from the
atmosphere through the contraction into the working section where its speed is 20 m/s,
and from there it flows through the diffuser into the fan, which returns it to the
atmosphere. Calculate the static and stagnation pressures at:
a. The working section
b. The inlet to the fan
C.
The exit from the fan, assuming no change in air speed across the fan.
d. Calculate the power supplied by the fan to the air.
Fan
V = 20 m/s
Working section
Diffuser
Contraction
Figure 2
12.40 A truncated nozzle with a 10 cm² exit area is supplied
from a helium reservoir in which the absolute pressure is first
130 kPa and then 350 kPa. The temperature in the reservoir is
28°C, and the back pressure is 100 kPa. Calculate the mass flow
rate of helium for the two reservoir pressures.
as density decreases, mass flow rate:
a. decrese
b. increase
c. stays the same
(provided the diameter of nozzle is constant)
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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- 6.A large blower for a furnace delivers 47,000 ft3/in (CFM) of air having a specific weight of 0.075 lb/ft3. Calculate the weight flow rat and mass flow rate.arrow_forwardDraw the different cases for the inlet and outlet velocity triangle for centrifugal compressor. Also draw the velocity triangle centrifugal compressor with consideration of the slip. Give a numerical example.arrow_forwardWith 280 K static temperature, 103 kPa static pressure and 167 m/sec speed, air heat is added to the duct. enters. Static pressure at the duct outlet is given as 65 kPa. How much heat has been added to the duct? How much more heat can be added to this channel without changing the conditions at the channel entrance?arrow_forward
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- Exercise 5.2 A Pelton wheel of 1.8 m in diameter and deflecting angle of the bucket 160° rotates at 400 rpm. The jet diameter is100 mm, the effective head to the nozzle is 135 m, and the nozzle coefficient is 0.97. Determine the a. output power if overall efficiency if the is 95%arrow_forwardTThe venturi of a simple carburetor has a throat diar the coefficient of flow is 0.8. The fuel orifice has a and the coefflicient of fuel flow is 0.65. The gasolin surface is 5 mm below the throat, calculate * of 20 mm and er of 1.14 mm when the nozzle (i) the air-fuel ratio for a pressure drop of 0.0. tip is ne arted (ii) the aiaeDW atio when the nozzle tip is taken into account (iii) the minimum velocity of air or critical air velocity requi red to start the fuel flow when the nozzle tip is provided. Assume the density of air and fuel as 1.20 and 750 kg/m respectively.arrow_forwardPlease attached photo. I have theoretically solved this using only equations I can’t find a way to solve without the mass flow rate or area of the inlet as a given.arrow_forward
- 3.15) An axial flow compressor stage has blade mean velocity of 200 m/s. The stage is to be designed for a stagnation temperature rise of 20 K and an axial velocity of 150 m/s, both constant from root to tip. The work done factor is 0.93. Assuming 50% reaction at mean radius, calculate the stage air angles at mean radius for free vortex design. = 17.07° = B2, B1 = 45.73° = a2 at mean radius].arrow_forwardThis is a fluid machine question. 1. A single stage centrifugal pump delivers 900 m^3/hr of sea water from a source where the water where the pressure is O.125 mpag. The pump discharges into surge tank rated at 300 psig, 3 m above the pump centerline. Loss of head due to friction in suction is 0.8 m and that in the discharge side is 3 m . Calculate the power required by the pump in kW. 2. An atmospheric tank at standard ambient conditions will serve as the source for a pump. It is calculated the length of the suction pipe is 200 m with friction factor of 0.02. What would be the minimum height of water level in the tank that must be maintained above the centerline of the pump to avoid cavitation? Pump specifications are as follows: Flow: 225 cu.m/hrHead: 20 mPower: 15 kNSuction flange and Pipe Diameter: 200 mmDischarge Flange and Pipe Diameter: 150mmNPSHa: 6.5 mNSPHr : 6marrow_forwardQ.3 Briefly explain why it is necessary for gases to flow in and out of a cylinder with minimum restriction. Q.4 Carry out research to find out what a flow bench can be used for when developing engines . Briefly explain your findings in the box below.arrow_forward
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