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Reverse Engineering of Passenger Jets – Classified Design Parameters 1 Master hesis Emiel De Grave Reverse Engineering of Passenger Jet Classified Design Parameters Fakultät Technik und Informatik Faculty of Engineering and Computer Science Department Fahrzeugtechnik und Flugzeugbau Department of Automotive and Aeronautical Engineering 2 Emiel De Grave Reverse Engineering of Passenger Jet Classified Design Parameters Hamburg University of Applied Sciences Faculty of Engineering and Computer Science Department of Automotive and Aeronautical Engineering Berliner Tor 9 20099 Hamburg Germany Author: Emiel De Grave Date: 25.08.2017 1. Examiner: Prof. Dr.-Ing. Dieter Scholz, MSME 3 DOI: https://doi.org/10.15488/9322 URN: https://nbn-resolving.org/urn:nbn:de:gbv:18302-aero2017-08-25.017 Associated URLs: https://nbn-resolving.org/html/urn:nbn:de:gbv:18302-aero2017-08-25.017 © This work is protected by copyright The work is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 4.0 International License: CC BY-NC-SA https://creativecommons.org/licenses/by-nc-sa/4.0 Any further request may be directed to: Prof. Dr.-Ing. Dieter Scholz, MSME E-Mail see: http://www.ProfScholz.de This work is part of: Digital Library - Projects & Theses - Prof. Dr. Scholz http://library.ProfScholz.de Published by Aircraft Design and Systems Group (AERO) Department of Automotive and Aeronautical Engineering Hamburg University of Applied Science This report is deposited and archived: Deutsche Nationalbiliothek (https://www.dnb.de) Repositorium der Leibniz Universität Hannover (https://www.repo.uni-hannover.de) Internet Archive (https://archive.org) Item: https://archive.org/details/TextDeGrave.pdf This report has associated published data in Harvard Dataverse: https://doi.org/10.7910/DVN/KPHTG7 4 Abstract This thesis explains how the classified design parameters of existing passenger jets can be de- termined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reverse engineering on the preliminary sizing and aiming for the classified design parameters as output, formulas are deviated to calculate the maximum lift coefficients, the maximum aerodynamic efficiency and the specific fuel consumption. The goal is to calculate these parameters, using only aircraft specifications that are made public by the manufacturer. The calculations are complex with mutual relations, iterative processes and op- timizations. Therefore, it is interesting to integrate everything in a tool. The tool is built in Microsoft Excel and explained in detail adding operating instructions. The program is executed for miscellaneous aeroplanes, supported with the necessary comments. Investigated aeroplanes are: Caravelle 10B (Sud-Aviation), Boeing 707-320C, BAe 146-200 (British Aerospance), A320-200 (Airbus), ‘Rebel’ (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X. 5 DEPARTMENT OF AUTOMOTIVE AND AERONAUTICAL ENGINEERING Reverse Engineering of Passenger Jet Classified Design Parameters Task for a Master thesis according to university regulations Background For competitive reasons manufacturers try to protect their product design with its inherent pa- rameters. This is done to protect company know-how and to maintain a possible design ad- vantage with respect to competing products. This principle is followed not only in case of mil- itary aircraft, but also for civil passenger jets. Parameters like maximum take-off mass are known as part of the certification process. Further parameters may be given, because they are uncritical or needed for aircraft operation. Other parameters like aerodynamic efficiency or en-gine efficiency are classified information. It would be beneficial to know such parameters to do own flight performance calculations or even redo a preliminary sizing of the aircraft under in-vestigation. This can be done out of interest, educational exercise or for a more in depth case study. Knowing classified parameters would enable a comparison of various similar contempo-rary aircraft or to investigate the evolution of aircraft with their parameters throughout aviation history. Reverse Engineering is a legal possibility to acquire the knowledge withheld. Task The task of this thesis is to investigate classified design parameters and find a method to calcu-late them from known aircraft parameters. This should be done by preliminary aircraft sizing in combination with reverse engineering. The tasks of the project are as follows: Review the basics of preliminary sizing of large (CS-25) passenger jet aircraft. Examine the concept of reverse engineering. Apply reverse engineering to preliminary sizing of large passenger jet aircraft. Construct a tool to enable reverse engineering to the given domain and level of detail. 6 Apply the tool to a number of interesting passenger jets. Analyze and interpret the results. Summarize the results in a case study for every investigated and reverse engineered aircraft. Compare the results of the case studies. The report has to be written in English based on German or international standards on report writing. 7 Declaration Herewith I affirm that this master thesis is entirely my own work. Where use has been made of the work of others, it has been fully acknowledged and referenced. Date Signature 24.08.2017 Emiel De Grave 8 Table of Content Page Abstract ...................................................................................................................................... 4 List of Figures .......................................................................................................................... 11 List of Tables ............................................................................................................................ 13 Nomenclature ........................................................................................................................... 14 List of Abbreviations and Acronyms ....................................................................................... 17 List of Definitions .................................................................................................................... 18 1 Introduction..................................................................................................... 20 1.1 Motivation......................................................................................................... 20 1.2 Definitions ........................................................................................................ 21 1.3 Objective of the Thesis ..................................................................................... 23 1.4 Literature Review ............................................................................................. 24 1.5 Structure of the Work ....................................................................................... 25 2 Aircraft Preliminary Sizing ........................................................................... 27 2.1 Landing ............................................................................................................. 28 2.2 Take-off ............................................................................................................ 29 2.3 Second Segment................................................................................................ 30 2.4 Missed Approach .............................................................................................. 31 2.5 Cruise ................................................................................................................ 32 2.5.1 Thrust-to-Weight Ratio ..................................................................................... 32 2.5.2 Wing Loading ................................................................................................... 35 2.6 Matching Chart and Design Point..................................................................... 37 2.7 Estimation of the Aircraft Design Parameters .................................................. 38 3 Reverse Engineering ....................................................................................... 41 3.1 Definition and Use ............................................................................................ 41 3.2 Permissibility to Perform Reverse Engineering ............................................... 42 3.3 Methodology of Reverse Engineering .............................................................. 43 3.4 STEP 1: Prescreening and Black-box ............................................................... 43 3.5 STEP 2: Functional Analysis ............................................................................ 44 3.6 Summary of the Reverse Engineering Process ................................................. 45 4 Reverse Engineering in Aircraft Preliminary Sizing .................................. 46 4.1 STEP 1: Prescreening and Black-box ............................................................... 46 4.2 STEP 2: Functional Analysis ............................................................................ 49 4.2.1 Maximum Lift Coefficient for
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