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TitleReverse Engineering of Passenger Jets - Classified Design Parameters
AuthorDe Grave, Emiel
Date2017
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ContributorScholz, Dieter
Languageeng
PublisherAircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences,
CoverageHamburg, Germany
Formattext/html
TypeText; Master Thesis; doc-type:text; doc-type:masterThesis; info:eu-repo/semantics/masterThesis; status-type:publishedVersion; info:eu-repo/semantics/publishedVersion
RightsCopyright by author
RightsCC BY-NC-SA
Rightshttps://creativecommons.org/licenses/by-nc-sa/4.0
Rightsinfo:eu-repo/semantics/openAccess
Subject(s)ddc:620; info:eu-repo/classification/ddc/629.13; Luftfahrt; Luftfahrzeug; Passagierflugzeug; Reverse Engineering; Aeronautics; Airplanes; Design; Reverse engineering; Luftfahrttechnik; Luftfahrzeug; Passagierflugzeug; Reverse Engineering; Luftfahrttechnik; Aerodynamik; Passagier; Flugzeug; Entwurf; Dimensionierung; Verifikation; Kraftstoffverbrauch; Start; Landung; Reiseflug; Gleitzahl; Auftriebsbeiwert; Aeronautics; Airplanes; Design; Reverse engineering; Aerodynamics; Aeroplanes; Computer software; Electronic; Spreadsheets; Verification (Logic); Airplanes--Fuel Consumption; Lift (Aerodynamics); Airplanes-Takeoff; Airplanes-Landing; Preliminary sizing; Glide ratio; L/D; Cruise
Abstract This thesis explains how the classified design parameters of existing passenger jets can be determined. 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 derived 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 optimizations. 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), "The Rebel" (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X.