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Range and Endurance Modeling of a Multi- Engine Aircraft with One Engine Inoperative (OEI)

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Range and Endurance Modeling of a Multi- Engine Aircraft with One Engine Inoperative (OEI) AUSTRALIAN DEFENCE THE UNIVERSITY OF FORCE ACADEMY NEW SOUTH WALES UNIVERSITY COLLEGE UNIVERSITY OF NEW SOUTH WALES AUSTRALIAN DEFENCE FORCE ACADEMY SCHOOL OF ENGINEERING AND INFORMATION TECHNOLOGY Range and endurance modeling of a multi- engine aircraft with one engine inoperative (OEI) THESIS Ye Naung Kyaw Kyaw z3345969 Supervisors: Dr Rikard Heslehurst, Dr Michael Harrap 26 November 2014 A thesis submitted for fulfillment of the requirements for the Degree of Master of Engineering in Aerospace (Research) ii | P a g e ABSTRACT When one of the engines on a multi-engine aircraft stops working the one engine inoperative (OEI) condition exists. This causes several negative effects to a number of performance variables in addition to the loss of engine thrust. The range and endurance of an aircraft are directly related to the quantity of the fuel available and the fuel consumption rate. This thesis was conducted to investigate range and endurance performance of a twin- engine jet aircraft of the Boeing 737 class, with One Engine Inoperative (OEI). The aims of the thesis also include analysis on All Engine Operating (AEO) performance including range and endurance performance, and turning flight performance. The modelling was mainly based on methods available in Jan Roskam textbooks and USAF DATCOM. The model used Thrust and Specific Fuel Consumption data presented in Jenkinson, L.R., Simpkin, P., and Rhodes, D., “Civil Jet Aircraft Design,” and detailed aircraft geometry properties given in Jane’s All the World Aircraft as well as materials made available in references. Required control surface deflections (ailerons and rudder) to maintain a moment balance in a given flight condition were determined. The increment in total drag (trim drag) on the aircraft due to these control surface deflections as well as the drag from wind milling inoperative engine were then added to the steady state drag. The total drag in One Engine Inoperative (OEI) condition was calculated to be increased by 30% at optimum range speed at 12,000 ft. The range and endurance were calculated using the Breguet Range and Endurance equations and then compared with numerical integration methods to verify the reliability of the equations. It was observed that sensitivity of weights in determining range performance was not significant with numerical integration methods yielding favourable results. It was found that the range performance with one engine inoperative (OEI) is approximately 2 to 5% superior while the endurance performance is about 11 to 14% superior to those with all engine operative (AEO) condition at flight levels where single engine flight is possible. The maximum one engine inoperative (OEI) altitude capability for the aircraft was estimated to be 12,000 feet. Speed reduction of about 15-20% of optimum range and endurance speeds with AEO is required to achieve optimum range and endurance performance in OEI condition for the aircraft. Validation of the results predicted for AEO and OEI conditions for the aircraft with performance data in Boeing 737-300 flight planning manual revealed that difference fell within 11% for both conditions for range. Finally, a further investigation into asymmetric thrust was conducted: turning performance (left turn vs. right turn) in a level coordinated flight condition with right OEI was analysed with turning on operative engine side (left turn with right OEI) proving a better option. ii | P a g e DISCLAIMER This thesis is an account of research undertaken by the author while being enrolled as a postgraduate student in fulfillment of the requirements for the degree of Master of Engineering in Aerospace at the University of New South Wales @ ADFA. Views expressed in this thesis are based on research and/or analysis conducted by the author during the candidature and do not represent the views of the University. iii | P a g e ACKNOWLEDGEMENTS It has been a long and winding journey over the past 3 years to arrive at the completion of this research project. First of all, I would like to thank my supervisor, Dr Rik Heslehurst, for generously dedicating his time to provide supervision, direction, inspiration and guidance as well as for leaving a comfortable space for my own ideas and creativity. His encouragement throughout the year has motivated me to finish this thesis to schedule and to the specifications that were initially planned. I would also like to thank Dr Michael Harrap, my co-supervisor for his valuable suggestions and feedback on my thesis even though he has retired from his position with the University since a while ago. I can never thank enough my parents back home in Burma, Capt. Kyaw Kyaw Oo Zin and Dr. Khin Mar Cho, and my sister, Dr. Khine Cho Kyaw for their relentless support in the pursuit of my life goals. My special thanks also go to my beloved wife, May Cho Chit Htwe, for her kind care, patient love, and constant motivation even from thousand “nautical” miles away helped me through the hardest time throughout the year. A special mention also goes to the academic staff on my annual review board, which provided constructive suggestions and comments on my progress throughout the candidature. I thank staff from the Academy Library for their thorough help on any assistance required with finding literature and texts necessary for the research. I would like to express my gratitude to all who have made the completion of this Thesis possible in any way. Thank you all. iv | P a g e CONTENTS ABSTRACT ....................................................................................................................... i DISCLAIMER ................................................................................................................. iii ACKNOWLEDGEMENTS ............................................................................................. iv CONTENTS ...................................................................................................................... v LIST OF FIGURES .......................................................................................................... x LIST OF TABLES ......................................................................................................... xiii CHAPTER 1: INTRODUCTION ..................................................................................... 1 1.1 Background ........................................................................................................ 1 1.2 Origin of the Research ........................................................................................ 2 1.3 Objectives of the Research ................................................................................. 2 1.4 Scope of the Thesis ............................................................................................. 4 1.5 Assumptions and Limitations ............................................................................. 4 1.6 Thesis Structure .................................................................................................. 5 1.7 Summary ............................................................................................................ 6 CHAPTER 2: LITERATURE REVIEW .......................................................................... 7 2.1 Introduction ........................................................................................................ 7 2.2 Aerodynamics ..................................................................................................... 7 2.2.1 Compressibility Effect ................................................................................ 8 2.2.2 Mach number .............................................................................................. 8 2.2.3 Airfoils, Wings and Lift .............................................................................. 8 2.2.4 Aspect Ratio ................................................................................................ 9 2.2.5 Lift for Wing-Body Interactions ............................................................... 10 2.2.6 Drag ........................................................................................................... 10 2.2.7 Aerodynamic Force Coefficients .............................................................. 11 2.3 Propulsion Systems .......................................................................................... 11 2.3.1 Specific Fuel Consumption (SFC) ............................................................ 14 2.3.2 Effects of Velocity and Altitude on Specific Fuel Consumption (SFC) ... 14 2.4 Equations of Motion ......................................................................................... 14 2.4.1 The Four Forces ........................................................................................ 14 2.4.2 Modelling the Equations of Motion .......................................................... 15 2.4.3 Reference Frames ...................................................................................... 15 2.5 Flight Dynamics and Control ........................................................................... 17 v | P a g e 2.5.1 Roll, Pitch and Yaw .................................................................................. 17 2.5.2 Control Surfaces ........................................................................................ 18 2.6 Range and Endurance ....................................................................................... 19 2.6.1 Range and Endurance - Constant AoA – Constant
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