Aviation Technology Name: Ryan Boyle. Subject name: Aircraft Aerodynamics‚ Structures and systems 1. Lecturer: Owen O’Sullivan. Year of submission: 12th of April 2016. Institute: Dublin institute of technology. Award: (BEng Tech level 7). Title: Aerodynamics‚ structures and systems questions. Name: Ryan Boyle. Award: Bachelor
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HARDWARE 3.1 INTRODUCTION Quadcopter is a flying vehicle with six degrees of freedom which uses four rotors to push air downwards and to create a thrust force for keeping the quadcopter on the air. The pilot or flight control unit will control the orientation and tile of the multicopter by reading the data from the sensors. Gyro‚ accelerometer‚ magnetometer or GPS can be used to sense the tile‚ orientation and position of the vehicle. It can be used in many applications merely by changing the sensors
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* Bernoulli’s Principle * Vacuum- A space entirely devoid of matter. * Vacuums don’t exist in the Earth’s atmosphere as air molecules are constantly bouncing off each-other. If a vacuum ever existed in the atmosphere it would be filled very quickly because there would be no resistance against the excited air molecules. * This phenomenon is the driving principle behind airplane wings. As wind blows over the wing (see picture below) there is a pressure differential between the
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ASCI 310: Aircraft Performance Research Project Objectives One of the requirements for this course is an Aircraft Performance Research Project that entails planning a flight from Denver International Airport (KDEN) to Chicago O’Hare International Airport (KORD) for a given aircraft‚ weather conditions‚ and assumptions. The objective is to apply what has been learned throughout this course. Drawing on aeronautics theory and using the performance charts and equations presented in the course‚
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1.On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will a) roll b) pitch nose up c) pitch nose down 2. Lift on a delta wing aircraft a) increases with an increased angle of incidence (angle of attack) b) decreases with an increase in angle of incidence (angle of attack c) does not change with a change in angle of incidence (angle of attack 3. On a straight wing aircraft‚ stall commences at the a) root on a high thickness ratio wing b) tip on
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SAEINDIA SAE Student Convention Welcome to Aero-modeling using Paper Wings! Paper Airplane models for college students! Enjoy Learn and align with Curriculum September 2008 Paper Wings Guidelines This may look ridiculous and appear to be a child’s play. As you use the kit and build your first plane‚ you will realize that it is not all that simple. Soon you will learn to make the plane to fly and discover the joy of flying. In the process you will learn the nuances of flying intuitively. This
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Oliver Breitenstein Development of a Flapping Wing Mechanism Semester Project Autonomous Systems Lab (ASL) Swiss Federal Institute of Technology (ETH) Zurich Supervision Dr. Samir Bouabdallah‚ Stefan Leutenegger and Prof. Dr. Roland Siegwart Spring Semester 2009 Contents Abstract Acknowledgements 1 Introduction 2 Review 2.1 Aerodynamics of flapping wings . 2.1.1 Wagner Effect . . . . . . . 2.1.2 Leading edge vortex . . . 2.1.3 Clap and fling mechanism 2.1.4 Rotational lift . . .
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ACKNOWLEDGMENT ACKNOWLEDGMENT Firstly the success of the project was by the grace of the Almighty. This Report would not have been possible without the essential and gracious support of many individuals. Firstly we thank our parents‚ for their unconditional love and support throughout and having faith in us. We thank Emirates Aviation college instructors and faculty members. The leadership of Mr. Omar Chafic‚ project supervisor and instructor‚ guided us throughout the process of the project
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Contents Introduction 2 Theory 3 LIFT COEFFICIENT 3 DRAG COEFFICIENT 4 VORTEX 6 SLENDER WING-BODY 6 VORTEX-LATTICE METHOD (VORLATM1) 7 POLHAMUS LEADING EDGE SUCTION ANALOGY 8 APPARATUS 11 Results and Procedures 11 Experimental data 12 Example of calculations 15 Discussion 24 Conclusion 32 References 33 Appendix 35 Introduction The aim of this experiment is to understand the non-linear aerodynamic characteristic of a slender wing-body (rocket shaped) by installing the slender wing-body inside
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Case Study Analysis Activity Title: Name: Date: Cause(s) of Accident The probable cause to the crash of American Airlines Flight 191 is the asymmetrical stall and the ensuing roll of the aircraft due to the un-commanded retraction of the left wing outboard leading edge slats and the loss of stall warning and slat disagreement indication systems‚ resulting from maintenance-induced damage leading to the separation of the number one engine and pylon assembly at a critical point during take-off
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