Mechanics of Flight. Warren F. Phillips. John Wiley & Sons, Inc. Professor Mechanical and Aerospace Engineering Utah State University WILEY
|
|
- Godwin Cameron
- 5 years ago
- Views:
Transcription
1 Mechanics of Flight Warren F. Phillips Professor Mechanical and Aerospace Engineering Utah State University WILEY John Wiley & Sons, Inc.
2 CONTENTS Preface Acknowledgments xi xiii 1. Overview of Aerodynamics Introduction and Notation Fluid Statics and the Atmosphere The Boundary Layer Concept Inviscid Aerodynamics Review of Elementary Potential Flows Incompressible Flow over Airfoils Trailing-Edge Flaps and Section Flap Effectiveness Incompressible Flow over Finite Wings Flow over Multiple Lifting Surfaces Inviscid Compressible Aerodynamics Compressible Subsonic Flow Supersonic Flow Problems Overview of Propulsion 2.1. Introduction 2.2. The Propeller 2.3. Propeller Blade Theory 2.4. Propeller Momentum Theory 2.5. Off-Axis Forces and Moments Developed by a Propeller 2.6. Turbojet Engines: The Thrust Equation 2.7. Turbojet Engines: Cycle Analysis 2.8. The Turbojet Engine with Afterburner 2.9. Turbofan Engines Concluding Remarks Problems Aircraft Performance Introduction Thrust Required Power Required Rate of Climb and Power Available Fuel Consumption and Endurance Fuel Consumption and Range Power Failure and Gliding Flight Airspeed, Wing Loading, and Stall 279 vii
3 VIII Contents 3.9. The Steady Coordinated Turn Takeoff and Landing Performance Accelerating Climb and Balanced Field Length Problems Longitudinal Static Stability and Trim Fundamentals of Static Equilibrium and Stability Pitch Stability of a Cambered Wing Simplified Pitch Stability Analysis for a Wing-Tail Combination Stick-Fixed Neutral Point and Static Margin Estimating the Downwash Angle on an Aft Tail Simplified Pitch Stability Analysis for a Wing-Canard Combination Effects of Drag and Vertical Offset Contribution of the Fuselage and Nacelles Contribution of Running Propellers Contribution of Jet Engines Problems Lateral Static Stability and Trim Introduction Yaw Stability and Trim Estimating the Sidewash Gradient on a Vertical Tail Estimating the Lift Slope for a Vertical Tail Roll Stability and Dihedral Effect Roll Control and Trim Requirements Longitudinal-Lateral Coupling Control Surface Sign Conventions Problems Aircraft Controls and Maneuverability 6.1. Longitudinal Control and Maneuverability 6.2. Effects of Structural Flexibility 6.3. Control Force and Trim Tabs 6.4. Stick-Free Neutral and Maneuver Points 6.5. Ground Effect, Elevator Sizing, and CG Limits 6.6. Stall Recovery 6.7. Lateral Control and Maneuverability 6.8. Aileron Reversal 6.9. Other Control Surface Configurations Airplane Spin Problems 7. Aircraft Equations of Motion 7.1. Introduction 7.2. Newton's Second Law for Rigid-Body Dynamics
4 Contents IX 7.3. Position and Orientation: The Euler Angle Formulation Rigid-Body 6-DOF Equations of Motion Linearized Equations of Motion Force and Moment Derivatives Nondimensional Linearized Equations of Motion Transformation of Stability Axes Inertial and Gyroscopic Coupling Problems Linearized Longitudinal Dynamics Fundamentals of Dynamics: Eigenproblems Longitudinal Motion: The Linearized Coupled Equations Short-Period Approximation Long-Period Approximation Pure Pitching Motion Summary Problems Linearized Lateral Dynamics Introduction Lateral Motion: The Linearized Coupled Equations Roll Approximation Spiral Approximation Dutch Roll Approximation Pure Rolling Motion Pure Yawing Motion Longitudinal-Lateral Coupling Nonlinear Effects Summary Problems Aircraft Handling Qualities and Control Response Introduction Pilot Opinion Dynamic Handling Quality Prediction Response to Control Inputs Nonlinear Effects and Longitudinal-Lateral Coupling Problems Aircraft Flight Simulation Introduction Euler Angle Formulations Direction-Cosine Formulation Euler Axis Formulation The Euler-Rodrigues Quaternion Formulation 874
5 Contents Quaternion Algebra Relations between the Quaternion and Other Attitude Descriptors Applying Rotational Constraints to the Quaternion Formulation Closed-Form Quaternion Solution for Constant Rotation Numerical Integration of the Quaternion Formulation Summary of the Flat-Earth Quaternion Formulation Aircraft Position in Geographic Coordinates Problems 928 Bibliography 931 Appendixes 941 A Standard Atmosphere, SI Units 941 B Standard Atmosphere, English Units 942 Index 943
FLIGHT DYNAMICS. Robert F. Stengel. Princeton University Press Princeton and Oxford
FLIGHT DYNAMICS Robert F. Stengel Princeton University Press Princeton and Oxford Preface XV Chapter One Introduction 1 1.1 ELEMENTS OF THE AIRPLANE 1 Airframe Components 1 Propulsion Systems 4 1.2 REPRESENTATIVE
More informationFundamentals of Airplane Flight Mechanics
David G. Hull Fundamentals of Airplane Flight Mechanics With 125 Figures and 25 Tables y Springer Introduction to Airplane Flight Mechanics 1 1.1 Airframe Anatomy 2 1.2 Engine Anatomy 5 1.3 Equations of
More informationAEROSPACE ENGINEERING
AEROSPACE ENGINEERING Subject Code: AE Course Structure Sections/Units Topics Section A Engineering Mathematics Topics (Core) 1 Linear Algebra 2 Calculus 3 Differential Equations 1 Fourier Series Topics
More informationIntroduction to Flight
l_ Introduction to Flight Fifth Edition John D. Anderson, Jr. Curator for Aerodynamics, National Air and Space Museum Smithsonian Institution Professor Emeritus University of Maryland Me Graw Higher Education
More informationDEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum
DEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum SEMESTER I AS5010 Engg. Aerodyn. & Flt. Mech. 3 0 0 3 AS5020 Elements of Gas Dyn. & Propln. 3 0 0 3 AS5030 Aircraft and Aerospace Structures
More informationFlight Dynamics, Simulation, and Control
Flight Dynamics, Simulation, and Control For Rigid and Flexible Aircraft Ranjan Vepa CRC Press Taylor & Francis Group Boca Raton London New York CRC Press is an imprint of the Taylor & Francis Group, an
More informationChapter 5 Performance analysis I Steady level flight (Lectures 17 to 20) Keywords: Steady level flight equations of motion, minimum power required,
Chapter 5 Performance analysis I Steady level flight (Lectures 17 to 20) Keywords: Steady level flight equations of motion, minimum power required, minimum thrust required, minimum speed, maximum speed;
More informationAircraft Performance, Stability and control with experiments in Flight. Questions
Aircraft Performance, Stability and control with experiments in Flight Questions Q. If only the elevator size of a given aircraft is decreased; keeping horizontal tail area unchanged; then the aircraft
More informationIntroduction to Flight Dynamics
Chapter 1 Introduction to Flight Dynamics Flight dynamics deals principally with the response of aerospace vehicles to perturbations in their flight environments and to control inputs. In order to understand
More informationIntroduction to Aircraft Flight. Mechanics
Introduction to Aircraft Flight. Mechanics i Performance, Static Stability, Dynamic Stability, Classical Feedback Control, and State-Space Foundations Second Edition Thomas R. Yechout with contributions
More informationFlight Dynamics and Control. Lecture 3: Longitudinal stability Derivatives G. Dimitriadis University of Liege
Flight Dynamics and Control Lecture 3: Longitudinal stability Derivatives G. Dimitriadis University of Liege Previously on AERO0003-1 We developed linearized equations of motion Longitudinal direction
More informationChapter 4 The Equations of Motion
Chapter 4 The Equations of Motion Flight Mechanics and Control AEM 4303 Bérénice Mettler University of Minnesota Feb. 20-27, 2013 (v. 2/26/13) Bérénice Mettler (University of Minnesota) Chapter 4 The Equations
More informationPRINCIPLES OF FLIGHT
1 Considering a positive cambered aerofoil, the pitching moment when Cl=0 is: A infinite B positive (nose-up). C negative (nose-down). D equal to zero. 2 The angle between the aeroplane longitudinal axis
More informationAircraft Design I Tail loads
Horizontal tail loads Aircraft Design I Tail loads What is the source of loads? How to compute it? What cases should be taken under consideration? Tail small wing but strongly deflected Linearized pressure
More information/ m U) β - r dr/dt=(n β / C) β+ (N r /C) r [8+8] (c) Effective angle of attack. [4+6+6]
Code No: R05322101 Set No. 1 1. (a) Explain the following terms with examples i. Stability ii. Equilibrium. (b) Comment upon the requirements of stability of a i. Military fighter aircraft ii. Commercial
More informationChapter 1 Lecture 2. Introduction 2. Topics. Chapter-1
Chapter 1 Lecture 2 Introduction 2 Topics 1.4 Equilibrium of airplane 1.5 Number of equations of motion for airplane in flight 1.5.1 Degrees of freedom 1.5.2 Degrees of freedom for a rigid airplane 1.6
More informationAircraft Flight Dynamics & Vortex Lattice Codes
Aircraft Flight Dynamics Vortex Lattice Codes AA241X April 14 2014 Stanford University Overview 1. Equations of motion 2. Non-dimensional EOM Aerodynamics 3. Trim Analysis Longitudinal Lateral 4. Linearized
More informationAE Stability and Control of Aerospace Vehicles
AE 430 - Stability and ontrol of Aerospace Vehicles Static/Dynamic Stability Longitudinal Static Stability Static Stability We begin ith the concept of Equilibrium (Trim). Equilibrium is a state of an
More informationFlight Dynamics and Control
Flight Dynamics and Control Lecture 1: Introduction G. Dimitriadis University of Liege Reference material Lecture Notes Flight Dynamics Principles, M.V. Cook, Arnold, 1997 Fundamentals of Airplane Flight
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 1 Introduction Aerospace Engineering Flight Mechanics Dr. ir. Mark Voskuijl 15-12-2012 Delft University of Technology Challenge
More informationIntroduction to Atmospheric Flight. Dr. Guven Aerospace Engineer (P.hD)
Introduction to Atmospheric Flight Dr. Guven Aerospace Engineer (P.hD) What is Atmospheric Flight? There are many different ways in which Aerospace engineering is associated with atmospheric flight concepts.
More informationFlight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and Orbital Mechanics Lecture 7 Equations of motion Mark Voskuijl Semester 1-2012 Delft University of Technology Challenge the
More informationContents. Preface... xvii
Contents Preface... xvii CHAPTER 1 Idealized Flow Machines...1 1.1 Conservation Equations... 1 1.1.1 Conservation of mass... 2 1.1.2 Conservation of momentum... 3 1.1.3 Conservation of energy... 3 1.2
More informationApril 15, 2011 Sample Quiz and Exam Questions D. A. Caughey Page 1 of 9
April 15, 2011 Sample Quiz Exam Questions D. A. Caughey Page 1 of 9 These pages include virtually all Quiz, Midterm, Final Examination questions I have used in M&AE 5070 over the years. Note that some
More informationSummer AS5150# MTech Project (summer) **
AE1 - M.Tech Aerospace Engineering Sem. Course No Course Name Lecture Tutorial Extended Tutorial Afternoon Lab Session Time to be spent outside of class 1 AS5010 Aerodynamics and Aircraft 3 0 0 0 6 9 performance
More informationPART ONE Parameters for Performance Calculations
PART ONE Parameters for Performance Calculations As an amateur designer/builder of homebuilt aircraft, you are chief aerodynamicist, structural engineer, dynamicist, mechanic, artist and draftsman all
More informationPerformance. 5. More Aerodynamic Considerations
Performance 5. More Aerodynamic Considerations There is an alternative way of looking at aerodynamic flow problems that is useful for understanding certain phenomena. Rather than tracking a particle of
More informationFUNDAMENTALS OF AERODYNAMICS
*A \ FUNDAMENTALS OF AERODYNAMICS Second Edition John D. Anderson, Jr. Professor of Aerospace Engineering University of Maryland H ' McGraw-Hill, Inc. New York St. Louis San Francisco Auckland Bogota Caracas
More informationStability and Control Some Characteristics of Lifting Surfaces, and Pitch-Moments
Stability and Control Some Characteristics of Lifting Surfaces, and Pitch-Moments The lifting surfaces of a vehicle generally include the wings, the horizontal and vertical tail, and other surfaces such
More informationDEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS B. Tech. Curriculum Semester wise credit distribution
DEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS B. Tech. Curriculum Semester wise credit distribution I II III IV V VI VII VIII Total 28 22 25 24 25 28 18 14 184 SEMESTER I AS1010 Introduction to Aerospace
More informationContents. I Introduction 1. Preface. xiii
Contents Preface xiii I Introduction 1 1 Continuous matter 3 1.1 Molecules................................ 4 1.2 The continuum approximation.................... 6 1.3 Newtonian mechanics.........................
More informationConsider a wing of finite span with an elliptic circulation distribution:
Question 1 (a) onsider a wing of finite span with an elliptic circulation distribution: Γ( y) Γo y + b = 1, - s y s where s=b/ denotes the wing semi-span. Use this equation, in conjunction with the Kutta-Joukowsky
More informationAerospace Engineering
A SET Booklet No. : AS - 15 Aerospace Engineering Duration of Test : Hours Max. Marks : 10 Hall Ticket No. Name of the Candidate : Date of Examination : OMR Answer Sheet No. : Signature of the Candidate
More informationIntroduction to Aerospace Engineering
4. Basic Fluid (Aero) Dynamics Introduction to Aerospace Engineering Here, we will try and look at a few basic ideas from the complicated field of fluid dynamics. The general area includes studies of incompressible,
More informationMODIFICATION OF AERODYNAMIC WING LOADS BY FLUIDIC DEVICES
Journal of KONES Powertrain and Transport, Vol. 21, No. 2 2014 MODIFICATION OF AERODYNAMIC WING LOADS BY FLUIDIC DEVICES Institute of Aviation Department of Aerodynamics and Flight Mechanics Krakowska
More informationExample of Aircraft Climb and Maneuvering Performance. Dr. Antonio A. Trani Professor
Example of Aircraft Climb and Maneuvering Performance CEE 5614 Analysis of Air Transportation Systems Dr. Antonio A. Trani Professor Example - Aircraft Climb Performance Aircraft maneuvering performance
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering 5. Aircraft Performance 5.1 Equilibrium Flight In order to discuss performance, stability, and control, we must first establish the concept of equilibrium flight.
More informationPreface. 2 Cable space accelerator 39
Contents Abstract Preface xiii xv 1 Space elevator, transport system for space elevator, 1 and tether system 1.1 Brief history 1 1.2 Short description 2 1.3 Transport system for the space elevator 5 1.4
More informationDegree Project in Aeronautics
DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 30 CREDITS STOCKHOLM, SWEDEN 2017 Degree Project in Aeronautics Conceptual design, flying and handling qualities of a supersonic transport aircraft.
More informationRotor reference axis
Rotor reference axis So far we have used the same reference axis: Z aligned with the rotor shaft Y perpendicular to Z and along the blade (in the rotor plane). X in the rotor plane and perpendicular do
More informationUniversity of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005
University of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005 Answer both questions. Question 1 is worth 30 marks and question
More informationFlight Vehicle Terminology
Flight Vehicle Terminology 1.0 Axes Systems There are 3 axes systems which can be used in Aeronautics, Aerodynamics & Flight Mechanics: Ground Axes G(x 0, y 0, z 0 ) Body Axes G(x, y, z) Aerodynamic Axes
More informationStability and Control Analysis in Twin-Boom Vertical Stabilizer Unmanned Aerial Vehicle (UAV)
International Journal of Scientific and Research Publications, Volume 4, Issue 2, February 2014 1 Stability and Control Analysis in Twin-Boom Vertical Stabilizer Unmanned Aerial Vehicle UAV Lasantha Kurukularachchi*;
More informationA SIMPLIFIED ANALYSIS OF NONLINEAR LONGITUDINAL DYNAMICS AND CONCEPTUAL CONTROL SYSTEM DESIGN
A SIMPLIFIED ANALYSIS OF NONLINEAR LONGITUDINAL DYNAMICS AND CONCEPTUAL CONTROL SYSTEM DESIGN ROBBIE BUNGE 1. Introduction The longitudinal dynamics of fixed-wing aircraft are a case in which classical
More informationAerospace Engineering undergraduate studies (course 2006)
Aerospace Engineering undergraduate studies (course 2006) The Bachelor of Science degree final exam problems and questions Specialization administrator: prof. Cezary Galiński Field of Study Aerospace Engineering
More informationModeling of a Small Unmanned Aerial Vehicle
Modeling of a Small Unmanned Aerial Vehicle A. Elsayed Ahmed, A. Hafez, A. N. Ouda, H. Eldin Hussein Ahmed, H. Mohamed Abd-Elkader Abstract Unmanned aircraft systems (UAS) are playing increasingly prominent
More informationWhat is flight dynamics? AE540: Flight Dynamics and Control I. What is flight control? Is the study of aircraft motion and its characteristics.
KING FAHD UNIVERSITY Department of Aerospace Engineering AE540: Flight Dynamics and Control I Instructor Dr. Ayman Hamdy Kassem What is flight dynamics? Is the study of aircraft motion and its characteristics.
More informationAeroelastic Gust Response
Aeroelastic Gust Response Civil Transport Aircraft - xxx Presented By: Fausto Gill Di Vincenzo 04-06-2012 What is Aeroelasticity? Aeroelasticity studies the effect of aerodynamic loads on flexible structures,
More informationGliding, Climbing, and Turning Flight Performance! Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2016
Gliding, Climbing, and Turning Flight Performance! Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2016 Learning Objectives Conditions for gliding flight Parameters for maximizing climb angle and rate
More informationConfiguration Aerodynamics
Configuration Aerodynamics William H. Mason Virginia Tech Blacksburg, VA The front cover of the brochure describing the French Exhibit at the Montreal Expo, 1967. January 2018 W.H. Mason CONTENTS i CONTENTS
More informationDefinitions. Temperature: Property of the atmosphere (τ). Function of altitude. Pressure: Property of the atmosphere (p). Function of altitude.
Definitions Chapter 3 Standard atmosphere: A model of the atmosphere based on the aerostatic equation, the perfect gas law, an assumed temperature distribution, and standard sea level conditions. Temperature:
More informationDesign, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I
Design, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I Copyright 00 by Dr. Jan Roskam Year of Print, 00 (Errata Revised August
More informationAerodynamics SYST 460/560. George Mason University Fall 2008 CENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCH. Copyright Lance Sherry (2008)
Aerodynamics SYST 460/560 George Mason University Fall 2008 1 CENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCH Copyright Lance Sherry (2008) Ambient & Static Pressure Ambient Pressure Static Pressure 2 Ambient
More informationTwo dimensional rate gyro bias estimation for precise pitch and roll attitude determination utilizing a dual arc accelerometer array
Rochester Institute of Technology RIT Scholar Works Theses Thesis/Dissertation Collections -- Two dimensional rate gyro bias estimation for precise pitch and roll attitude determination utilizing a dual
More informationMissile Interceptor EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P Ryan Donnan, Herman Ryals
EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P- 2011121203 Ryan Donnan, Herman Ryals Georgia Institute of Technology School of Aerospace Engineering Missile Interceptor December 12, 2011 EXTROVERT ADVANCED
More information( ) (where v = pr ) v V
Problem # The DOF idealized wing whose cross-section is shown in Figure. has leading edge and trailing edge control surfaces. There is no initial angle of attack when the two control surfaces are undeflected.
More informationJet Aircraft Propulsion Prof. Bhaskar Roy Prof. A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay
Jet Aircraft Propulsion Prof. Bhaskar Roy Prof. A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay Lecture No. #03 Jet Engine Basic Performance Parameters We are talking
More informationVishwakarma Institute of Technology. Honors in Aerospace Engineering
Page 1 of 15 Bansilal Ramnath Agarwal Charitable Trust s Vishwakarma Institute of Technology (An Autonomous Institute affiliated to Savitribai Phule Pune University formerly University of Pune) Structure
More informationν δ - 1 -
ν δ - 1 - δ ν ν δ ν ν - 2 - ρ δ ρ θ θ θ δ τ ρ θ δ δ θ δ δ δ δ τ μ δ μ δ ν δ δ δ - 3 - τ ρ δ ρ δ ρ δ δ δ δ δ δ δ δ δ δ δ - 4 - ρ μ ρ μ ρ ρ μ μ ρ - 5 - ρ τ μ τ μ ρ δ δ δ - 6 - τ ρ μ τ ρ μ ρ δ θ θ δ θ - 7
More informationStability and Control
Stability and Control Introduction An important concept that must be considered when designing an aircraft, missile, or other type of vehicle, is that of stability and control. The study of stability is
More informationFREQUENCY DOMAIN FLUTTER ANALYSIS OF AIRCRAFT WING IN SUBSONIC FLOW
FREQUENCY DOMAIN FLUTTER ANALYSIS OF AIRCRAFT WING IN SUBSONIC FLOW Ms.K.Niranjana 1, Mr.A.Daniel Antony 2 1 UG Student, Department of Aerospace Engineering, Karunya University, (India) 2 Assistant professor,
More informationMODELING OF A SMALL UNMANNED AERIAL VEHICLE
MODELING OF A SMALL UNMANNED AERIAL VEHICLE AHMED ELSAYED AHMED Electrical Engineering Dept., Shoubra Faculty of Engineering, Benha University, Qaliuobia, Egypt (Telephone: +201007124097), Email: eng_medoelbanna
More informationChapter 5 Lecture 19. Performance analysis I Steady level flight 3. Topics. Chapter-5
Chapter 5 Lecture 19 Performance analysis I Steady level flight 3 Topics 5.8 Influence of level flight analysis on airplane design 5.9 Steady level flight performance with a given engine 5.10 Steady level
More informationAero-Propulsive-Elastic Modeling Using OpenVSP
Aero-Propulsive-Elastic Modeling Using OpenVSP August 8, 213 Kevin W. Reynolds Intelligent Systems Division, Code TI NASA Ames Research Center Our Introduction To OpenVSP Overview! Motivation and Background!
More informationGliding, Climbing, and Turning Flight Performance Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018
Gliding, Climbing, and Turning Flight Performance Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018 Learning Objectives Conditions for gliding flight Parameters for maximizing climb angle and rate
More informationQuiz 2 May 18, Statement True False 1. For a turbojet, a high. gives a high thermodynamic efficiency at any compression ratio.
Quiz 2 May 18, 2011 16.50 Propulsion Systems Spring 2011 Two hours, open book, open notes TRUE-FALSE QUESTIONS Justify your answer in no more than two lines. 4 points for correct answer and explanation
More informationCompressible Potential Flow: The Full Potential Equation. Copyright 2009 Narayanan Komerath
Compressible Potential Flow: The Full Potential Equation 1 Introduction Recall that for incompressible flow conditions, velocity is not large enough to cause density changes, so density is known. Thus
More informationApplication of larger wings to create more lift force in aeroplane Lokendra Bhati 1,Rajat Malviya 2 1 B.E.in mechanical engineering, I.I.ST.
Application of larger wings to create more lift force in aeroplane Lokendra Bhati 1,Rajat Malviya 2 1 B.E.in mechanical engineering, I.I.ST. Indore, India 2 B.E.in mechanical engineering, I.I.ST. Indore,
More informationStolSpeed Vortex Generators on a Harmon Rocket II Flight Test Report
StolSpeed Vortex Generators on a Harmon Rocket II Flight Test Report Vernon Little Version 1.1, November 29, 2016 Summary StolSpeed Vortex Generators were installed on a Harmon Rocket II (C-GVRL). Flight
More informationModelling of Opposed Lateral and Longitudinal Tilting Dual-Fan Unmanned Aerial Vehicle
Modelling of Opposed Lateral and Longitudinal Tilting Dual-Fan Unmanned Aerial Vehicle N. Amiri A. Ramirez-Serrano R. Davies Electrical Engineering Department, University of Calgary, Canada (e-mail: namiri@ucalgary.ca).
More informationAircraft stability and control Prof: A. K. Ghosh Dept of Aerospace Engineering Indian Institute of Technology Kanpur
Aircraft stability and control Prof: A. K. Ghosh Dept of Aerospace Engineering Indian Institute of Technology Kanpur Lecture- 05 Stability: Tail Contribution and Static Margin (Refer Slide Time: 00:15)
More informationAirfoils and Wings. Eugene M. Cliff
Airfoils and Wings Eugene M. Cliff 1 Introduction The primary purpose of these notes is to supplement the text material related to aerodynamic forces. We are mainly interested in the forces on wings and
More informationTurn Performance of an Air-Breathing Hypersonic Vehicle
Turn Performance of an Air-Breathing Hypersonic Vehicle AIAA Aircraft Flight Mechanics Conference Derek J. Dalle, Sean M. Torrez, James F. Driscoll University of Michigan, Ann Arbor, MI 4809 August 8,
More informationTrim 2D. Holly Lewis University of Colorado Center for Aerospace Structures April 29, 2004
rim D Holly Lewis University of Colorado Center for Aerospace Structures April 9 004 Overview rimming an Aircraft in D Forces and Moments AERO-rimD Assumptions Capabilities Results Conclusions Future wor
More informationMultidisciplinary Design Optimization Of A Helicopter Rotor Blade
Ryerson University Digital Commons @ Ryerson Theses and dissertations 1-1-2010 Multidisciplinary Design Optimization Of A Helicopter Rotor Blade Michael G. Leahy Ryerson University Follow this and additional
More informationHigh Speed Aerodynamics. Copyright 2009 Narayanan Komerath
Welcome to High Speed Aerodynamics 1 Lift, drag and pitching moment? Linearized Potential Flow Transformations Compressible Boundary Layer WHAT IS HIGH SPEED AERODYNAMICS? Airfoil section? Thin airfoil
More informationAE 451 Aeronautical Engineering Design I Aerodynamics. Prof. Dr. Serkan Özgen Dept. Aerospace Engineering December 2017
AE 451 Aeronautical Engineering Design I Aerodynamics Prof. Dr. Serkan Özgen Dept. Aerospace Engineering December 2017 Lift curve 2 Lift curve slope 3 Subsonic lift curve slope C Lα = 2 + 4 + AR2 β 2 η
More informationAlternative Expressions for the Velocity Vector Velocity restricted to the vertical plane. Longitudinal Equations of Motion
Linearized Longitudinal Equations of Motion Robert Stengel, Aircraft Flig Dynamics MAE 33, 008 Separate solutions for nominal and perturbation flig paths Assume that nominal path is steady and in the vertical
More informationAE 451 Aeronautical Engineering Design I Aerodynamics. Prof. Dr. Serkan Özgen Dept. Aerospace Engineering December 2015
AE 451 Aeronautical Engineering Design I Aerodynamics Prof. Dr. Serkan Özgen Dept. Aerospace Engineering December 2015 Lift curve 2 Lift curve slope 3 Subsonic lift curve slope C Lα = 2 + 4 + AR2 β 2 η
More informationUse of Compliant Hinges to Tailor Flight Dynamics of Unmanned Aircraft
JOURNAL OF AIRCRAFT Use of Compliant Hinges to Tailor Flight Dynamics of Unmanned Aircraft Emily A. Leylek and Mark Costello Georgia Institute of Technology, Atlanta, Georgia 30332 DOI: 10.2514/1.C033056
More informationStability Characteristics of Micro Air Vehicles from Experimental Measurements
29th AIAA Applied Aerodynamics Conference 27-3 June 211, Honolulu, Hawaii AIAA 211-3659 Stability Characteristics of Micro Air Vehicles from Experimental Measurements Daniel V. Uhlig and Michael S. Selig
More informationLecture No. # 09. (Refer Slide Time: 01:00)
Introduction to Helicopter Aerodynamics and Dynamics Prof. Dr. C. Venkatesan Department of Aerospace Engineering Indian Institute of Technology, Kanpur Lecture No. # 09 Now, I just want to mention because
More informationQ. 1 Q. 25 carry one mark each.
GATE 015 Q. 1 Q. 5 carry one mark each. Q.1 The partial differential equation (A) linear and first order (C) non-linear and first order u u + = 0 is t x (B) linear and second order (D) non-linear and second
More informationChapter 1 Introduction (Lectures 1,2 and 3)
Chapter 1 Introduction (Lectures 1,2 and 3) Keywords : Importance of stability and control analysis ; brief historical background ; basic concepts static stability, dynamic stability, longitudinal, lateral
More informationSyllabus for AE3610, Aerodynamics I
Syllabus for AE3610, Aerodynamics I Current Catalog Data: AE 3610 Aerodynamics I Credit: 4 hours A study of incompressible aerodynamics of flight vehicles with emphasis on combined application of theory
More informationAim. Unit abstract. Learning outcomes. QCF level: 6 Credit value: 15
Unit T23: Flight Dynamics Unit code: J/504/0132 QCF level: 6 Credit value: 15 Aim The aim of this unit is to develop learners understanding of aircraft flight dynamic principles by considering and analysing
More informationDynamics and Control Preliminary Examination Topics
Dynamics and Control Preliminary Examination Topics 1. Particle and Rigid Body Dynamics Meirovitch, Leonard; Methods of Analytical Dynamics, McGraw-Hill, Inc New York, NY, 1970 Chapters 1-5 2. Atmospheric
More informationIndex Downloaded by on March 16, DOI: / Book DOI: /4.
Index four-degrees-of-freedom motion simulation, 88 six-dof motion, 141 six-degrees of freedom, 141 accelerations due to changing body axis rotation rates, 54 accelerometers, 95 aerodynamic derivatives
More informationMODELLING AND CONTROL OF A SYMMETRIC FLAPPING WING VEHICLE: AN OPTIMAL CONTROL APPROACH. A Thesis JUSTIN PATRICK JACKSON
MODELLING AND CONTROL OF A SYMMETRIC FLAPPING WING VEHICLE: AN OPTIMAL CONTROL APPROACH A Thesis by JUSTIN PATRICK JACKSON Submitted to the Office of Graduate Studies of Texas A&M University in partial
More informationLecture AC-1. Aircraft Dynamics. Copy right 2003 by Jon at h an H ow
Lecture AC-1 Aircraft Dynamics Copy right 23 by Jon at h an H ow 1 Spring 23 16.61 AC 1 2 Aircraft Dynamics First note that it is possible to develop a very good approximation of a key motion of an aircraft
More informationDynamic Modeling of Fixed-Wing UAVs
Autonomous Systems Laboratory Dynamic Modeling of Fixed-Wing UAVs (Fixed-Wing Unmanned Aerial Vehicles) A. Noth, S. Bouabdallah and R. Siegwart Version.0 1/006 1 Introduction Dynamic modeling is an important
More informationExtended longitudinal stability theory at low Re - Application to sailplane models
Extended longitudinal stability theory at low Re - Application to sailplane models matthieu.scherrer@free.fr November 26 C L C m C m W X α NP W X V NP W Lift coefficient Pitching moment coefficient Pitching
More information1. Fluid Dynamics Around Airfoils
1. Fluid Dynamics Around Airfoils Two-dimensional flow around a streamlined shape Foces on an airfoil Distribution of pressue coefficient over an airfoil The variation of the lift coefficient with the
More informationFlight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and orbital mechanics Flight Mechanics practice questions Dr. ir. Mark Voskuijl 20-11-2013 Delft University of Technology Challenge
More informationDrag Computation (1)
Drag Computation (1) Why drag so concerned Its effects on aircraft performances On the Concorde, one count drag increase ( C D =.0001) requires two passengers, out of the 90 ~ 100 passenger capacity, be
More informationFundamentals of Aerodynamics
Fundamentals of Aerodynamics Fourth Edition John D. Anderson, Jr. Curator of Aerodynamics National Air and Space Museum Smithsonian Institution and Professor Emeritus University of Maryland Me Graw Hill
More informationANALYSIS OF AUTOPILOT SYSTEM BASED ON BANK ANGLE OF SMALL UAV
ANALYSIS OF AUTOPILOT SYSTEM BASED ON BANK ANGLE OF SMALL UAV MAY SAN HLAING, ZAW MIN NAING, 3 MAUNG MAUNG LATT, 4 HLA MYO TUN,4 Department of Electronic Engineering, Mandalay Technological University,
More informationDesign, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I
Design, Analysis and Research orporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight ontrols Part I opyright 995 by Dr. Jan Roskam Year of Print, 995 (Errata Revised August 7,
More informationRobot Dynamics Fixed-wing UAVs: Dynamic Modeling and Control
Robot Dynamics Fixed-wing UAVs: Dynamic Modeling and Control 151-0851-00 V Marco Hutter, Roland Siegwart, and Thomas Stastny 05.12.2017 1 Contents Fixed-wing UAVs 1. ntroduction 2. Aerodynamic Basics 3.
More informationAircraft Structures Design Example
University of Liège Aerospace & Mechanical Engineering Aircraft Structures Design Example Ludovic Noels Computational & Multiscale Mechanics of Materials CM3 http://www.ltas-cm3.ulg.ac.be/ Chemin des Chevreuils
More information