Good knowledge of physics (mechanics, in particular), analytical mechanics and basic tools of calculus are necessary.

The course is aimed at introducing the student to the methods for estimating aircraft performance as a function of aerodynamic configuration and propulsion system. Based on models derived from first principles, the students will learn how to evaluate fixed-wing aircraft range and endurance, flight envelope, take-off and landing distance, climb and turn performance. The course is mainly focused on rigid fixed-wing aircraft, but a few notion on rotorcraft performance and space flight mechanics (orbits, orbit perturbations and orbital maneuvers) are also provided. Tutorials will allow the students to apply the notions learned to representative examples and case studies, developing the capabilitiy of solving simple problems and write computer programs that allow for a systematic analysis of the relation between aircraft characteristics and its expected behavior.

At the end of the course the student is expected to

1) understand the relations between aircraft configuration, mission requirements and expected performance;

2) evaluate performance from the knowledge of aerodynamic and propulsion characteristics;

3) understand basic features of rotary wing aircraft configurations and evaluate their performance;

4) understand basic features of space flight mechanics;

5) handle mathematical tools and write simple software programs in order to develop the ability for quantitative analysis of aircraft behavior as a function of design parameters.

The course is delivered with class and laboratory activities, in three different forms:

- standard class lectures, where the teacher presents methods and models; students are encouraged to participate by discussing validity of the assumptions at the basis of the models and physical meanings of the results derived from the analysis performed; example: derive the expressions for minimum and maximum airspeed of a turbojet aircraft;

- tutorial classes, during which problems are stated, where the students refine their understanding, by numerically evaluating aircraft performance from geometric, propulsion and aerodynamics characteristics; the teacher supports the class by recalling relevant models and highlighting the procedure; some calculations (e.g. for a different set of parameters) can be proposed to the students as homework; example: evaluate minimum and maximum airspeed of a turbojet aircraft at a given altitude, knowing maximum thrust-to-weight ratio and aerodynamic coefficients;

- computer lab. classes, where students are required to write simple computer programs for performing parametric analysis, in order to assess aircraft performance for a wider range of design variables; example: plot the flight envelope of a turbojet aircraft in the altitude vs airspeed plane. Results from homework and conputer lab classes will be collected in a report to be delivered and discussed during the oral exam.

The written test is divided into 2 parts.

Part 1, to be completed in 90 minutes, without using books or lecture notes:

- 2 theoretical questions, that require analytic evaluation of some physical facts regarding aircraft performance and/or dynamics;

- 2 descriptive questions, where the student is required to demonstrate his understanding of some specific facts of aircraft configuration, systems or features of its dynamic behaviour.

 Part 2, to be completed in 60 minutes, using books and/or lecture notes:

- 2 problems, where the students prove their ability in quantitavely evaluating aircraft performance from its geometrical, inertial and aerodynamic characteristics.

The use of programmable devices and/or devices connected to the internet is strictly forbidden. Calculations can be performed by means of a non-programmable scientific calculator

Introduction to Aeronautics

Darrol Stinton. The Anatomy of the Aeroplane, 2nd ed., Blackwell science, 1998

E. Torenbeek. Flight Physiscs, Springer, 2009

Holt Ashley. Engineering Analysis of Flight Vehicles, Dover, 1992

Barnes W. McCormick. Aerodynamics, Aeronautics, and Flight Mechanics, J. Wiley & Sons, 1994

Richard Von Mises, Theory of Flight, Dover, 1959

Daniel P. Raymer. Aircraft design: a conceptual approach, 4th ed., AIAA Education Series, 2006

 

Performance

Francis J. Hale. Introduction to Aircraft Performance, Selection and Design. J. Wiley & Sons, 1984

J. D. Anderson jr. Aircraft Performance and design, McGraw Hill, 1999

J.B. Russell. Performance and Stability of Aircraft, Arnold, 1996

Nguyen X. Vinh. Flight Mechanics of High Performance Aircraft, Cambridge University Press, 1995

D.R., Kermode (R.H., Philpott and A.C. Barnard editors). Mechanics of Flight, 11th ed. Prentice Hall, 2006

 

Handbooks on space flight mechanics (orbital dynamics and orbit maneuvers)

R. Battin. An Introduction to the Mathematics and Methods of Astrodynamics, AIAA Education Series, 1987

Roger B. Bate, Donald D. Mueller, and Jerry E. White, Fundamentals of Astrodynamics, Dover, 1971

D.A. Vallado. Fundamentals of Astrodynamics and Applications, Microcosm Press, 2013

F.P.J. Rimrott, Introductory Orbit Dynamics, Vieweg, 1989

 

In Italiano

A. Lausetti e F. Filippi. Elementi di Meccanica del Volo. Levrotto e Bella, 1956

M. Calcara, Elementi di Dinamica del Velivolo, Edizioni CUEN, Napoli, 1988

M. Venuti, Aerodinamica Oggi, TOTEM, 2002

G. Guglieri. Introduzione alla Meccanica del Volo. CELID, 2005

G. Mengali e A. Quarta. Fondamenti di Meccanica del Volo Spaziale,Pisa University Press, 2013