Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.18P
(The purpose of this problem is to calculate a two-dimensional expanding supersonic flow and compare it with the analogous quasi-one-dimensional flow in Problem 10.15.) Consider a two-dimensional duct with a straight horizontal lower wall, and a straight upper wall inclined upward through the angle
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Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure and 100°C temperature. State the necessary assumptions and calculate:
d) With the specified inlet velocity a gas is flowing isentropically in the converging duct. At the throat if we assume that the velocity is supersonic, how does the mass flow rate be affected compared to sonic velocity at the throat. How could supersonic velocity can be achieved in this case?
Note :
(The properties of air at room temperature are R = 0.287 kPa.m3/kg.K and k = 1.4.)
please answer my question , please help me , don't use hand write , I need by Ms word
Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure and 100°C temperature. State the necessary assumptions and calculate, (a) stagnation temperature (b) stagnation pressure, and (c) stagnation density.(d) With the specified inlet velocity a gas is flowing isentropically in the converging duct. At thethroat if we assume that the velocity is supersonic, how does the mass flow rate be affectedcompared to sonic velocity at the throat. How could supersonic velocity can be achieved in thiscase?
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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