Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 2, Problem 2.13P
Consider the subsonic compressible flow over the wavy wail treated in Example 2.1. Derive the equation for the velocity potential for this flow as a function of x and y.
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Problem 2
An unconfined supersonic flow passes over the contoured wall shown below. The wall segment
AB is a 30° arc of a circle of radius R and wall segment is a 30° arc of a circle of radius R.
Calculate the wall static pressures at B and C.
Mo. = 2.0
P., = 1 bar
==
A
B
R
30°
30° R
C
* Your answer is incorrect.
A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of 2000 m/s, and a
3
density of 1.0 kg/m in the test section. Find the temperature and pressure in the test section and the upstream
stagnation conditions. The fluid is helium.
Te = i 217
Pe=
To = i
12.1
868.325
PO = i 387.2
K
kPa
K
kPa
he reservoir pressure and temperature for a Laval nozzle are 5 atm [abs] and 520 K,respectively. The flow is isentropically expanded to supersonic speed at the nozzle exitwith area Ae = 4in2. If the exit-to-throat area ratio is 2.295, calculate the followingexit properties: g) ̇mass flow rate
gamma = 1.4, R = 287 J/kgK
Please show all work
Chapter 2 Solutions
Fundamentals of Aerodynamics
Ch. 2 - Consider a body of arbitrary shape. If the...Ch. 2 - Consider an airfoil in a wind tunnel (i.e., a wing...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - Consider a velocity field where the radial and...Ch. 2 - Consider a velocity field where the x and y...Ch. 2 - The velocity field given in Problem 2.3 is called...Ch. 2 - The velocity field given in Problem 2.4 is called...Ch. 2 - Is the flow field given in Problem 2.5...Ch. 2 - Consider a flow field in polar coordinates, where...
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