Theory of Aerospace Propulsion

1st Edition

Authors: Pasquale Sforza
Hardcover ISBN: 9781856179126
eBook ISBN: 9780123848895
Imprint: Butterworth-Heinemann
Published Date: 21st October 2011
Page Count: 704
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Table of Contents


Chapter 1. Idealized Flow Machines

1.1. Conservation Equations

1.2. Flow Machines with No Heat Addition: The Propeller

1.3. Flow Machines with P = 0 and Q = Constant: The Turbojet, Ramjet, and Scramjet

1.4. Flow Machines with P = 0, Q = Constant, and A0 = 0: The Rocket

1.5. The Special Case of Combined Heat and Power: The Turbofan

1.6. Force Field for Air-Breathing Engines

1.7. Conditions for Maximum Thrust

1.8. Example: Jet and Rocket Engine Performance

1.9. Nomenclature

Chapter 2. Quasi-One-Dimensional Flow Equations

2.1. Introduction

2.2. Equation of State

2.3. Speed of Sound

2.4. Mach Number

2.5. Conservation of Mass

2.6. Conservation of Energy

2.7. Example: Heating Values for Different Fuel–Oxidizer Combinations

2.8. Conservation of Species

2.9. Conservation of Momentum

2.10. Impulse Function

2.11. Stagnation Pressure

2.12. Equations of Motion in Standard Form

2.13. Example: Flow in a Duct with Friction

2.14. Nomenclature

Chapter 3. Idealized Cycle Analysis of Jet Propulsion Engines

3.1. Introduction

3.2. General Jet Engine Cycle

3.3. Ideal Jet Engine Cycle Analysis

3.4. Ideal Turbojet in Maximum Power Take-Off

3.5. Ideal Turbojet in High Subsonic Cruise in The Stratosphere

3.6. Ideal Turbojet in Supersonic Cruise in The Stratosphere

3.7. Ideal Ramjet in High Supersonic Cruise in The Stratosphere

3.8. Ideal Turbofan in Maximum Power Take-Off

3.9. Ideal Turbofan in High Subsonic Cruise in The Stratosphere

3.10. Ideal Internal Turbofan in Supersonic Cruise in The Stratosphere

3.11. Real Engine Operations

3.12. Nomenclature

Chapter 4. Combustion Chambers for Air-Breathing Engines

4.1. Combustion Chamber Attributes



Readers of this book will be able to:
utilize the fundamental principles of fluid mechanics and thermodynamics to analyze aircraft engines,
understand the common gas turbine aircraft propulsion systems and be able to determine the applicability of each, 
perform system studies of aircraft engine systems for specified flight conditions,
perform preliminary aerothermal design of turbomachinery components, and 
conceive, analyze, and optimize competing preliminary designs for conventional and unconventional missions.

Key Features

  • Early coverage of cycle analysis provides a systems perspective, and offers context for the chapters on turbomachinery and components
  • Broader coverage than found in most other books - including coverage of  propellers, nuclear rockets, and space propulsion - allows analysis and design of more types of propulsion systems
  • In depth, quantitative treatments of the components of jet propulsion engines provides the tools for evaluation and component matching for optimal system performance
  • Worked examples and end of chapter exercises provide practice for analysis, preliminary design, and systems integration




Aerospace or mechanical engineers working in gas turbines, turbomachinery, aircraft propulsion and rocket propulsion.  Undergraduate and graduate level students in aerospace or mechanical engineering studying aerospace propulsion or turbomachinery.


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About the Authors

Pasquale Sforza Author

Pasquale Sforza received his PhD from the Polytechnic Institute of Brooklyn in 1965. He has taught courses related to commercial airplane design at the Polytechnic Institute of Brooklyn and the University of Florida. His research interests include propulsion, gas dynamics, and air and space vehicle design. Dr. Sforza has also acted as Co-Editor of the Journal of Directed Energy and Book Review Editor for the AIAA Journal. His previous books include Theory of Aerospace Propulsion (Butterworth-Heinemann, 2011) and Commercial Airplane Design Principles, (Butterworth-Heinemann, 2014)

Affiliations and Expertise

Department of Mechanical and Aerospace Engineering, University of Florida, Gainesville, FL, USA