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Tesi etd-01262015-123546


Thesis type
Tesi di laurea magistrale
Author
COSTA, GIULIO
URN
etd-01262015-123546
Title
Aerodynamic optimization of a large PrandtlPlane configuration
Struttura
INGEGNERIA CIVILE E INDUSTRIALE
Corso di studi
INGEGNERIA AEROSPAZIALE
Commissione
relatore Dott. Rizzo, Emanuele
relatore Ing. Oliviero, Fabrizio
relatore Dott. Cipolla, Vittorio
relatore Prof. Frediani, Aldo
Parole chiave
  • PrandtlPlane
  • optimization
  • aerodynamic
Data inizio appello
03/03/2015;
Consultabilità
parziale
Data di rilascio
03/03/2018
Riassunto analitico
The present Thesis deals with the application of optimization methods to the preliminary<br>design of a large PrandtlPlane® freighter and with graphical tools to visualize the most<br>interesting configurations.<br>The conceptual design of the PrandtlPlane® freighter has been developed by the Department<br>of Civil and Industrial Engineering – Aerospace Section of the University of Pisa<br>and it is summarized in Chapter 1; the installation of a third lifting surface is described<br>and its effects are foreseen for a large aircraft: improving the maneuverability and the<br>stability is the main aim, without penalizing aerodynamic efficiency and weights.<br>The preliminary study needs a graphical software package (ASD) and an aerodynamic optimizer<br>(AEROSTATE): both of them have been performed using MATLAB® routines.<br>Chapter 2 briefly describes ASD. Local and global optimization methods, together with<br>their implementation in AEROSTATE, are shown in Chapter 3. The aerodynamic solver<br>(AVL) is based on the Vortex lattice Method; despite of its simplicity, the reliability of<br>the results on a PrandtlPlane® configuration has been proved in previous studies: thus,<br>this method is the compromise between accuracy and computational simplicity.<br>AEROSTATE provides results as MATLAB® structured variables and they are transferred<br>to ASD by means INTERFACE, a MATLAB® environment that is developed in<br>this thesis and it is presented in Chapter 4.<br>In Chapter 5, analyses and results are shown: sensitivity studies have been made to the<br>front wing loading, to the rear wing loading, to the bulks length, to the wingspan and<br>to the fins height. The purpose of these studies is to understand how the designer can<br>improve the aerodynamic efficiency in cruise and to obtain a feasible structure.<br>Finally, Chapter 6 explains that many configurations, with different wings arrangements,<br>satisfy low speed constraints, i.e. the landing is possible with low angles of attack, and<br>the trim conditions on the longitudinal plane are met, when flaps and slats are deflected,<br>by means suitable elevators. Conclusions and future developments are collected at the<br>end of this paper.
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