Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.18P
The stagnation temperature on the Apollo vehicle at Mach 36 as it entered the atmosphere was 11.000 K. a much different value than predicted in Problem 8.17 for the case of a calorically perfect gas with a ratio of specific heats equal to 1.4. The difference is due to chemical reactions that occur in air at these high temperatures—dissociation and ionization. The analyses in this book assuming a calorically perfect gas with constant specific heats are not valid for such chemically reacting flows. However, as an engineering approximation, the calorically perfect gas results are sometimes applied with a lower value of the ratio of specific heats, a so-called “effective gamma.” in order to try to simulate the effects of high temperature chemically reacting flows. For the condition stated in this problem, calculate the value of the effective gamma necessary to yield a temperature of 11,000 K at the stagnation point. Assume the freestream temperature is 300 K.
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32. A perfect gas expands polytropically with an initial volume and temperature of 0.06 m3 and 147°C. If the final volume and temperature are 0.21 m3 and 21°C, what is the value of polytropic index n?
3. Consider a vehicle moving at a velocity of 1,000 mps through air and hydrogen. The specific gas constant of hydrogen is 4,157 ???−?⁄. Assume T = 300 K.
a. Calculate the Mach number of the vehicle in air.
b. Calculate the Mach number of the vehicle in hydrogen.
Using the following information, determine the vapor pressure of water at
300 °C. Note: We started this problem in week 6 lecture 3. Please refer to the lecture to get started on this
problem. You only need to show your work starting from where the lecture left off.
H₂0 at T = 179.88 degrees C
the vapor pressure is PSAT = 10 bar.
The enthalpy of vaporization is 2014.59 kJ/kg
V = 0.1944 m³/kg
V¹ = 0.001127 m³/kg
The equation we left off on in class was,
cpf 1
[P²
psat dpsat
pi psat
Tf
1 ∆vapH (TF 1
RAZ
Ti
dT
T2a
Chapter 8 Solutions
Fundamentals of Aerodynamics
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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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