Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.9P
Consider an oblique shock generated at a compression corner with a deflection angle
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The driver and driven gases in a shock tube are both air at 300 K. Assume p4/p1 = 8.006. After the
diaphragm is broken, an incident shock wave is propagating into the driven section and an incident
expansion wave is propagating into the driver section. If the strength of the incident shock (p2/p1) is 2.6,
a. Calculate the strength of the incident expansion wave (p3/p4).
b. Calculate the induced mass motion velocity behind the expansion wave.
c. Find the propagation velocity of the head expansion wave.
d. Find the propagation velocity of the tail expansion wave.
Consider an oblique shock generated at a compression corner with adeflection angle θ = 18.2◦. A straight horizontal wall is present above thecorner, as shown . If the upstream flow has the propertiesM1 = 3.2, p1 = 1 atm and T1 = 520◦R, calculate M3, p3, and T3 behindthe reflected shock from the upper wall. Also, obtain the angle whichthe reflected shock makes with the upper wall.
Q.3. Airflow at M1 = 2.2 takes a compression turn of 12° and then another turn of
angle as shown in the figure. What is the maximum value of 0max for the second
shock to be attached?
%3D
M1 =
= 2.2
emax?
12°
Chapter 9 Solutions
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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- = 1-An oblique shock forms in air at an angle of 0 30°. Before passing through the shock, the air has a temperature of 60°F, a pressure of 10 psia, and is traveling at M = 2.6. elocity components before and after (a) Compute the normal and tangential the shock. HEGE Of and (b) Determine the temperature and pressure after the shock. (c) What is the deflection angle?arrow_forwardQ.3. Airflow at M1 = 2.2 takes a compression turn of 12° and then another turn of angle as shown in the figure. What is the maximum value of 0max for the second shock to be attached? 3 M1 = 2.2 Omax (2 12°arrow_forward2. Determine the back pressure necessary for a normal shock to appear at the exit of a converging-diverging nozzle, as shown in the figure. Assume y = 1.4. Pr = 1.0 MPa T₁ = 800 K рь A exit A throat = 2.0arrow_forward
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- 0/ QI diesel engine has a clearance volume is 0.00025m and bore and stroke of 152.5mm and 200mm, respectively. A charge of air at 100kPa and 20C is taken into the cylinder and compressed adiabatically y=1.4. After combustion at constant pressure the temperature is 1090°C. The expansion which follows is adiabatic. Find a- the temperature and the pressure at the end of compression b- the temperature and pressure after expansion c- the ideal thermal efficiency of the engine (591°Č,4400kPa,227°C,188kPa,0.633)arrow_forwardQ1. A turbojet aircraft flying at speed of 1645 km/h and altitude of 9000 m. A supersonic intake was designed with a conical center body, which generated one oblique shock wave and normal shock wave at the inlet of the aircraft. The deflection of the conical center body is a 10°. Calculate the fluid flow properties and velocity at the aircraft inlet of the intake. Assume a weak solution. Take: R= 0.287 kJ/kg K, and Cp=0.9 kJ/kg K.arrow_forwardA radial flow machine has an impeller with inlet diameter D1= 0.025m, outlet diameter D2=0.077m, inlet blade angle β1=40º, outlet blade angle β2=10º, and N=950 rpm. The angle of attack at the inlet is 90º Neglect the effects of slip conditions and losses, and assuming the radial flow components of the absolute velocity are the same at the inlet and the outlet. Calculate the specific work of the machine in J/kg Is this machine a pump or a turbine?arrow_forward
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