Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.19P
Prove that the total pressure is constant throughout an isentropic flow.
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Dry saturated steam at a pressure of 8 bar enters a convergent divergent nozzle and leaves it at a pressure of 1.5 bar. If the flow is isentropic and if the corresponding expansion index is 1.135, Determine the ratio of crosssectional area at exit and throat for maximum discharge
Q.2. Air flows through a constant-area duct is connected to a reservoir at a
temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown
in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach
number and the mass flow rate for a back pressure of 0 kPa.
q= 250 kJ/kg
P.= 500 kPa
T; = 500°C
p. = 0 kPa
D=0.02m
Q.2. Air flows through a constant-area duct is connected to a reservoir at a
temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown
in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach
number and the mass flow rate for a back pressure of 0 kPa.
q = 250 kJ/kg
P. = 500 kPa
T, = 500°C
Po = 0 kPa
D = 0.02m
Chapter 8 Solutions
Fundamentals of Aerodynamics
Ch. 8 - Consider air at a temperature of 230 K. Calculate...Ch. 8 - The temperature in the reservoir of a supersonic...Ch. 8 - At a given point in a flow, T=300K,p=1.2atm, and...Ch. 8 - At a given point in a flow, T=700R,p=1.6atm, and...Ch. 8 - Consider the isentropic flow through a supersonic...Ch. 8 - Consider the isentropic flow over an airfoil. The...Ch. 8 - The flow just upstream of a normal shock wave is...Ch. 8 - The pressure upstream of a normal shock wave is 1...Ch. 8 - The entropy increase across a normal shock wave is...Ch. 8 - The how just upstream of a normal shock wave is...
Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Repeat Problems 8.11 and 8.12 using (incorrectly)...Ch. 8 - Derive the Rayleigh Pitot tube formula, Equation...Ch. 8 - On March 16, 1990, an Air Force SR-71 set a new...Ch. 8 - In the test section of a supersonic wind tunnel, a...Ch. 8 - When the Apollo command module returned to earth...Ch. 8 - The stagnation temperature on the Apollo vehicle...Ch. 8 - Prove that the total pressure is constant...
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