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Performance calculations can be classified into three main types: lift, thrust and slope. Firstly, since the lift profile is known and unmodifiable from the time an aircraft is designed, the mass at a given speed or the speed at a given mass must be determined. Then, once the thrust of the engines and the mass are known, the slope must be calculated. Finally, once the slope is known (for example, level flight) as well as the mass, it is necessary to deduce the thrust; this is the position of the throttle control lever that ensures balance.

The corresponding consumption must then be defined. Performance specifications for customer aircraft, such as manoeuvrability, fuel consumption, maintenance, safety and testability, have become ever more demanding with each generation of equipment. Major technical advances have been required: wing profiles, engines, materials to reduce mass, etc. This book presents a theoretical approach to flight mechanics that makes it possible to grasp the subject and links it with the empirical approach of manufacturers.

Table of Contents

  1. Cover
  2. Title Page
  3. Copyright
  4. Foreword
  5. Introduction
  6. 1 Use of Aerodynamic Forces to Control the Trajectory of an Aircraft
  7. 2 Aerodynamic Forces and Moments and their Derivatives
  8. 3 Wind Tunnel
  9. 4 Trihedron
  10. 5 Movement of a Solid
  11. 6 Aircraft Characteristics
  12. 7 Aircraft Simulation Model
  13. 8 Processing of Trajectography Information
  14. 9 Quaternion Methods
  15. Glossary
  16. List of Abbreviations
  17. References
  18. Index
  19. End User License Agreement
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