Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.20P
Consider a Mach 3 flow at 1 atm pressure initially moving over a flat horizontal surface. The flow then encounters a 20 degree expansion corner, followed by a 20 degree compression corner that turns the flow back to the horizontal. Calculate the pressure of the flow downstream of the compression corner. Note: You will find that the pressure downstream of the compression corner is different from the pressure upstream of the expansion corner, even though the upstream and downstream flows are in the same direction, namely horizontal. Why?
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MMB 241 - Dynamics of Particles
Tutorial 1
Topic: Kinematics of Particles:- Displacement, velocity and acceleration of particles.
QUESTIONS
1. If v = (4t+5) m/s, where t is in seconds, determine a when t = 2 s.
2. If s = (2t³) m, where t is in seconds, determine v when t = 2 s.
3. If a = 2 m/s², determine v at s = 4 m if v = 3 m/s at s = 0.
4. If a = 4 m/s², determines when t = 3 s if v = 2 m/s and s = 2 m when t=0.
5. A particle moves along a straight line such that its position is defined by s = (t² - 6t + 5) m.
Determine the average velocity, the average speed, and the acceleration of the particle
when t = 6 s.
6. A particle is moving with a velocity of vo when s=0 and t=0. If it is subjected to a
deceleration of a = -kv³ where k is a constant, determine its velocity and position as
functions of time.
7. A particle travels along a straight-line path such that in 4s it moves from an initial position
SA = -8 m to a position SB = +3 m. Then in…
3-141
(3-113)
Chapter 9 Solutions
Loose Leaf for Fundamentals of Aerodynamics
Ch. 9 - A slender missile is flying at Mach 1.5 at low...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Equation (8.80) does not hold for an oblique shock...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Consider the flow over a 22.2 half-angle wedge. If...Ch. 9 - Consider a flat plate at an angle of attack a to a...Ch. 9 - A 30.2 half-angle wedge is inserted into a...Ch. 9 - Consider a Mach 4 airflow at a pressure of 1 atm....Ch. 9 - Consider an oblique shock generated at a...Ch. 9 - Consider the supersonic flow over an expansion...
Ch. 9 - A supersonic flow at M1=1.58 and p1=1atm expands...Ch. 9 - A supersonic flow at M1=3,T1=285K, and p1=1atm is...Ch. 9 - Consider an infinitely thin flat plate at an angle...Ch. 9 - Consider a diamond-wedge airfoil such as shown in...Ch. 9 - Consider sonic flow. Calculate the maximum...Ch. 9 - Consider a circular cylinder (oriented with its...Ch. 9 - Consider the supersonic flow over a flat plate at...Ch. 9 - (The purpose of this problem is to calculate a...Ch. 9 - Repeat Problem 9.18, except with =30. Again, we...Ch. 9 - Consider a Mach 3 flow at 1 atm pressure initially...Ch. 9 - The purpose of this problem is to explain what...
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