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Empennage Statistics and Sizing Methods for Dorsal Fins

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Empennage Statistics and Sizing Methods for Dorsal Fins AERO_TN_TailSizing_13-04-15 Aircraft Design and Systems Group (AERO) Department of Automotive and Aeronautical Engineering Hamburg University of Applied Sciences Berliner Tor 9 D - 20099 Hamburg Empennage Statistics and Sizing Methods for Dorsal Fins Priyanka Barua Tahir Sousa Dieter Scholz 2013-04-15 Technical Note AERO_TN_TailSizing_13-04-15 Dokumentationsblatt 1. Berichts-Nr. 2. Auftragstitel 3. ISSN / ISBN AERO_TN_TailSizing Airport2030 --- (Effizienter Flughafen 2030) 4. Sachtitel und Untertitel 5. Abschlussdatum Empennage Statistics and 2013-04-15 Sizing Methods for Dorsal Fins 6. Ber. Nr. Auftragnehmer AERO_TN_TailSizing 7. Autor(en) (Vorname, Name, E-Mail) 8. Förderkennzeichen Priyanka Barua 03CL01G Tahir Sousa 9. Kassenzeichen Dieter Scholz 810302101951 10. Durchführende Institution (Name, Anschrift) 11. Berichtsart Aircraft Design and Systems Group (AERO) Technische Niederschrift Department Fahrzeugtechnik und Flugzeugbau 12. Berichtszeitraum Fakultät Technik und Informatik 2012-10-15 – 2013-04-15 Hochschule für Angewandte Wissenschaften Hamburg (HAW) Berliner Tor 9, D - 20099 Hamburg 13. Seitenzahl 145 14. Auftraggeber (Name, Anschrift) 15. Literaturangaben Bundesministerium für Bildung und Forschung (BMBF) 81 Heinemannstraße 2, D - 53175 Bonn - Bad Godesberg 16. Tabellen 48 Projektträger Jülich Forschungszentrum Jülich GmbH 17. Bilder Wilhelm-Johnen-Straße, D - 52438 Jülich 76 18. Zusätzliche Angaben Sprache: Englisch. URL: http://Reports_at_AERO.ProfScholz.de 19. Kurzfassung Dieser Bericht beschreibt verbesserte Methoden zur Abschätzung von Parametern des Höhen- und Seitenleitwerks. Weiterhin werden parameter der Rückenflossen aus den Parametern des a aSeitenleitwerks abgeleitet um den Vorentwurf zu unterstützen. Basis sind Statistiken aufbauend auf aDaten, die aus Dreiseitenansichten gewonnen werden. Die betrachteten Parameter sind Leitwerksvolumenbeiwert,a Streckung, Zuspitzung, Pfeilwinkel, relative Profildicke für Höhen- und Seitenleitwerk,a sowie die Profiltiefe und Spannweite von Höhen- und Seitenruder. Der Bericht a schlägt z.B. vor die relative Dicke des Höhenleitwerkes etwa als 81 % der relativen Dicke des a Flügels anzusetzen. Die Methode zur Abschätzung der Parameter der Rückenflosse erreicht eine aGenaui gkeit von 18%. a a20. Deskriptoren / Schlagwörter aLeitwerk, Seitenleitwerk, Höhenleitwerk, Rückenflosse, Seitenruder, Höhenruder, Flugzeugentwurf a 21. Bezugsquelle AERO, Department F+F, HAW Hamburg, Berliner Tor 9, D - 20099 Hamburg 22. 23. 24. Preis Sicherheitsvermerk keiner Dokumentationsblatt nach DIN 1422 Teil 4 2 AERO_TN_TailSizing_13-04-15 Report Documentation Page 1. Report-Number 2. Project Title 3. ISSN / ISBN AERO_TN_TailSizing Airport2030 N/A (Effizienter Flughafen 2030) 4. Title and Subtitle 5. Report Date Empennage Statistics and 2013-04-15 Sizing Methods for Dorsal Fins 6. Performing Org. Rep. No AERO_TN_TailSizing 7. Author(s) (First Name, Last Name) 8. Contract Code Priyanka Barua 03CL01G Tahir Sousa 9. Payment Number Dieter Scholz 810302101951 10. Performing Agency (Name, Address) 11. Report Type Aircraft Design and Systems Group (AERO) Technical Note Department of Automotive and Aeronautical Engineering 12. Time Period Faculty of Engineering and Computer Science 2012-10-15 – 2013-04-15 Hamburg University of Applied Sciences (HAW) Berliner Tor 9, D - 20099 Hamburg 13. Number of Pages 145 14. Sponsoring / Monitoring Agency (Name, Address) 15. Number of References Federal Ministry of Education and Research (BMBF) 81 Heinemannstraße 2, D - 53175 Bonn - Bad Godesberg 16. Number of Tables Projektträger Jülich 48 Forschungszentrum Jülich GmbH 17. Number of Figures Wilhelm-Johnen-Straße, D - 52438 Jülich 76 18. Supplementary Notes Language: English; URL: http://Reports_at_AERO.ProfScholz.de 19. Abstract This report aims to suggest better estimations for tail parameter sizes and develop relations between the dorsal fin and vertical tail to aid in conceptual design. This is done mainly through statistical a analyses based on measurements from 3-view drawings developing previously unexplored relation- a aships. Parameter analyzed for horizontal and vertical tail are tail volume coefficient, aspect ratio, ataper ratio, sweep angle and relative thickness of the airfoil, furthermore relative chord and span for elevatora and rudder. This report proposes for example to take the relative thickness ratio of the hori- zontala tail as approximately 81% that of the wing. The final methods of dorsal fin sizing were found a to achieve an average error of 18%. a 20. Subject Terms a empennage, tail, dorsal, fin, horizontal, vertical, rudder, elevator, aircraft, design, sizing, statistic a a a21. Distribution AERO, Department F+F, HAW Hamburg, Berliner Tor 9, D - 20099 Hamburg 22. Classification / Availability 23. 24. Price unclassified - unlimited Dokumentationsblatt nach DIN 1422 Teil 4 3 AERO_TN_TailSizing_13-04-15 Abstract In the tail sizing stage of conceptual design, it is aimed to estimate the different tail parameter sizes as accurately as possible. The first problem dealt with in this report is to suggest better estimations for tail parameter sizes. Data produced from measurements of aircraft 3-view dia- grams and data of new aircraft are averaged with data published by previous authors to im- prove these estimates. Moreover, this report tries to develop previously unexplored relation- ships to aid in estimation. Parameters analyzed are volume coefficient, aspect ratio, taper ra- tio, quarter chord sweep angle, relative thickness of the airfoil and control surface chords and spans. This report proposes ranges of 3.38 to 5.34 and 0.27 to 0.51 for a horizontal tail aspect ratio and taper ratio respectively for jet transport aircraft. Also, it claims that the relative thickness ratio of the horizontal tail is approximately 81% that of the wing. The second prob- lem dealt with is to develop relations between the dorsal fin and vertical tail to aid in concep- tual design of the dorsal fin. A dorsal fin is an extension in front of the vertical tail stretching along the fuselage with a sweep angle higher than that of the vertical tail. A vertical tail needs to cope with high side slip angles in order to protect the aircraft. A dorsal fin can help to in- crease the stall angle of the isolated vertical tail. Vertical tails with low leading edge sweep benefit from an addition of a dorsal fin. The dorsal fin leading edge sweep is typically around 72˚ for jet and 75˚ for propeller aircraft. The proposed sizing method is based on statistics of regional jet and propeller airliners for the root chord of the dorsal fin as a function of the root chord of the tail. The final methods were found to achieve an average error of 18%. This re- port can therefore be useful to a designer attempting to estimate parameter sizes for the tail and dorsal fin of an aircraft during the conceptual design phase. 4 AERO_TN_TailSizing_13-04-15 Table of Contents List of Figures.................................................................................................. 7 List of Tables ................................................................................................. 10 List of Symbols .............................................................................................. 12 List of Abbreviations ..................................................................................... 13 Terms and Definitions.................................................................................... 14 1 Introduction ............................................................................................... 20 1.1 Motivation ..................................................................................................... 20 1.2 Definitions ..................................................................................................... 21 1.3 Objectives ...................................................................................................... 22 1.4 Methodology ................................................................................................. 23 1.5 Literature ....................................................................................................... 24 1.6 Structure of the Report ................................................................................... 25 2 State of the Art ............................................................................................. 27 2.1 General Characteristics of Vertical Tails, Dorsal and Ventral Fins ................. 27 2.2 Aerodynamic Characteristics of Vertical Tails ............................................... 30 2.3 Aerodynamic Characteristics of Dorsal Fins .................................................. 38 2.4 Types of Dorsal Fins ...................................................................................... 43 2.5 Tail Sizing ..................................................................................................... 45 2.5.1 Tail Area and Tail Span ................................................................................. 45 2.5.2 Tail Volume Coefficients ............................................................................... 50 2.5.3 Aspect Ratio .................................................................................................. 54 2.5.4 Taper Ratio .................................................................................................... 57 2.5.5 Quarter Chord Sweep Angle .........................................................................
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