Definitions. Temperature: Property of the atmosphere (τ). Function of altitude. Pressure: Property of the atmosphere (p). Function of altitude.

Size: px
Start display at page:

Download "Definitions. Temperature: Property of the atmosphere (τ). Function of altitude. Pressure: Property of the atmosphere (p). Function of altitude."

Transcription

1 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: Property of the atmosphere (τ). Function of altitude. Pressure: Property of the atmosphere (p). Function of altitude. Density: Property of the atmosphere (ρ). Function of altitude. Troposphere: Atmosphere from sea level to the tropopause (h =36,089 ft). Standard sea level conditions: Conditions at sea level used to define the standard atmosphere. Stratosphere: Atmosphere between h=36,089 ft and h=105,000 ft. Tropopause: Dividing line between the stratosphere and the troposphere, h=36,089 ft. Speed of sound: Property of the atmosphere (a). Function of temperature. Viscosity: Property of the atmosphere (µ). Function of temperature. Exponential atmosphere: An approximate standard atmosphere based on the assumption of constant temperature. ρ = ρ s exp( h/λ) Isothermal atmosphere: A constant temperature atmosphere. Same as exponential atmosphere. Lift coefficient: Nondimensional lift, C L = L/ qs. Drag coefficient: Nondimensional drag, C D = D/ qs.

2 Wing planform area: From the top view of an airplane, it is the area S of the wing extended from the fuselage centerline to the wing tip (outside of tip tanks if present). Mach number: Ratio of airplane velocity to speed of sound at the altitude the airplane is operating, M = V/A. Reynolds number: Ratio of inertia forces to viscous forces, R e = ρv l/µ Drag polar: The relationship between C D and C L, C D = C D (C L, M, R e ). Also called aero- Lift-to-drag ratio: Ratio of lift to drag E = L/D. dynamic efficiency. Aerodynamic efficiency: Lift to drag ratio, E = L/D. Zero-lift angle of attack: The angle of attack α 0L at which C L = 0, α 0L Lift-curve slope: The slope of the C L versus α curve, C Lα Basic symmetric airfoil: The thickness distribution of the airfoil without camber. Camber line: the line between the upper and lower sides of a cambered airfoil. Center of pressure: The intersection of the airfoil aerodynamic force line of action and the chord. Peak suction: The point on the chord where the minimum pressure occurs, x ps. Ideal lift coefficient: Lift coefficient of an airfoil where the minimum drag occurs. Thickness ratio: Ratio of the maximum thickness to the chord of an airfoil. 2

3 Root chord: The chord of the wing at the body reference line, c r. Tip chord: The chord at the tip of the wing (outside the tip tank if present), c t. Semi-span: The distance b/2 between the root chord and the tip chord. Sweep: The angle Λ that a particular chord line makes with the y axis. Aspect ratio: A nondimensional quantity which indicates the slenderness of a wing, A = b 2 /S Taper ratio: The nondimensional quantity c t /c r of a wing. Mean aerodynamic chord: The chord of an equivalent rectangular wing, c. Equivalent rectangular wing: A rectangular wing which has the same lift and the same moments about the x and y axes. Wing incidence: Angle i W between the wing chord plane and the body x axis. Wing chord plane: For a wing with no twist and the same airfoil shape along the span, the surface formed by the chords is a plane. Friction drag coefficient: The friction drag is the part of the drag caused by skin friction acting over the surface of the airplane, also called parasite drag. Wave drag coefficient: The wave drag is the part of the drag caused by the appearance of shock waves on a wing. The shock waves cause the boundary layer to separate. Induced drag coefficient: The induced drag is the component of the drag induced by the rotational flow about the wing tip vortices. Equivalent parasite area method: The parasite area is the area touched by the air flow over an airplane. Equivalent parasite area is parasite area 3

4 corrected for Mach number, interference, thickness, etc. Skin friction coefficient: The equivalent parasite area divided by the planform area. Compressibility factor: Gives the effect of Mach number on the equivalent parasite area. Interference factor. Gives the effect of interference effects on the equivalent parasite area. Form factor: Gives the effect of wing and body thickness on the equivalent parasite area: Fineness ratio: For a body shape, it is the length of the body divided by the maximum diameter. Wetted area: The wetted area is the surface area of an airplane which is touched by the air flow, S wet Mach number for drag divergence: The Mach number at which the drag begins to increase rapidly do to the appearance of shock waves, M D Oswald s efficiency factor: It gives the increase in induced drag due to the difference between an elliptic planform and another planform, e Parabolic drag polar: The drag polar that has the shape of a parabola, C D = C D0 (M) + K(M)C 2 L. Zero-lift drag coefficient: It is the drag coefficient C D0 the parabolic drag polar when C L = 0. associated with Induced drag coefficient: It is the drag coefficient KC 2 L associated with the parabolic drag polar. Induced drag factor: It is the term K in the parabolic drag polar. Corrected thrust: data. A nondimensional thrust used to represent thrust 4

5 Corrected specific fuel consumption: A nondimensional specific fuel consumption used to represent specific fuel consumption data. Corrected engine speed: A nondimensional engine speed used to represent engine speed data. Ideal subsonic airplane: A subsonic jet airplane characterized by a parabolic drag polar with constant coefficients, thrust independent of velocity, and specific fuel consumption independent of velocity and power setting. Ideal SBJ: The ideal representation of the airplane (SBJ) in App. A. 5

Given the water behaves as shown above, which direction will the cylinder rotate?

Given the water behaves as shown above, which direction will the cylinder rotate? water stream fixed but free to rotate Given the water behaves as shown above, which direction will the cylinder rotate? ) Clockwise 2) Counter-clockwise 3) Not enough information F y U 0 U F x V=0 V=0

More information

Introduction to Aerospace Engineering

Introduction 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 information

Airfoils and Wings. Eugene M. Cliff

Airfoils 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 information

Air Loads. Airfoil Geometry. Upper surface. Lower surface

Air Loads. Airfoil Geometry. Upper surface. Lower surface AE1 Jha Loads-1 Air Loads Airfoil Geometry z LE circle (radius) Chord line Upper surface thickness Zt camber Zc Zl Zu Lower surface TE thickness Camber line line joining the midpoints between upper and

More information

APPENDIX C DRAG POLAR, STABILITY DERIVATIVES AND CHARACTERISTIC ROOTS OF A JET AIRPLANE (Lectures 37 to 40)

APPENDIX C DRAG POLAR, STABILITY DERIVATIVES AND CHARACTERISTIC ROOTS OF A JET AIRPLANE (Lectures 37 to 40) APPENDIX C DRAG POLAR, STABILITY DERIVATIVES AND CHARACTERISTIC ROOTS OF A JET AIRPLANE (Lectures 37 to 40 E.G. TULAPURKARA YASHKUMAR A. VENKATTRAMAN REPORT NO: AE TR 2007-3 APRIL 2007 (REVISED NOVEMBER

More information

High Speed Aerodynamics. Copyright 2009 Narayanan Komerath

High 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 information

INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad

INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad - 500 043 AERONAUTICAL ENGINEERING TUTORIAL QUESTION BANK Course Name : LOW SPEED AERODYNAMICS Course Code : AAE004 Regulation : IARE

More information

for what specific application did Henri Pitot develop the Pitot tube? what was the name of NACA s (now NASA) first research laboratory?

for what specific application did Henri Pitot develop the Pitot tube? what was the name of NACA s (now NASA) first research laboratory? 1. 5% short answers for what specific application did Henri Pitot develop the Pitot tube? what was the name of NACA s (now NASA) first research laboratory? in what country (per Anderson) was the first

More information

Drag Computation (1)

Drag 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 information

Fundamentals of Airplane Flight Mechanics

Fundamentals 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 information

MDTS 5705 : Aerodynamics & Propulsion Lecture 2 : Missile lift and drag. G. Leng, MDTS, NUS

MDTS 5705 : Aerodynamics & Propulsion Lecture 2 : Missile lift and drag. G. Leng, MDTS, NUS MDTS 5705 : Aerodynamics & Propulsion Lecture 2 : Missile lift and drag 2.1. The design of supersonic airfoils For efficient lift generation at subsonic speeds, airfoils look like : So why can t a similar

More information

Drag Analysis of a Supermarine. Spitfire Mk V at Cruise Conditions

Drag Analysis of a Supermarine. Spitfire Mk V at Cruise Conditions Introduction to Flight Aircraft Drag Project April 2016 2016 Drag Analysis of a Supermarine Spitfire Mk V at Cruise Conditions Nicholas Conde nicholasconde@gmail.com U66182304 Introduction to Flight Nicholas

More information

Flight Vehicle Terminology

Flight 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 information

AE 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 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 information

Chapter 5 Wing design - selection of wing parameters 2 Lecture 20 Topics

Chapter 5 Wing design - selection of wing parameters 2 Lecture 20 Topics Chapter 5 Wing design - selection of wing parameters Lecture 0 Topics 5..4 Effects of geometric parameters, Reynolds number and roughness on aerodynamic characteristics of airfoils 5..5 Choice of airfoil

More information

To highlight the change in drag with lift: Drag = Zero-Lift Drag + Lift-Dependent Drag + Compressibility Drag

To highlight the change in drag with lift: Drag = Zero-Lift Drag + Lift-Dependent Drag + Compressibility Drag Drag Drag Bookkeeping Drag may be divided into components in several ways: To highlight the change in drag with lift: Drag = Zero-Lift Drag + Lift-Dependent Drag + Compressibility Drag To emphasize the

More information

Consider a wing of finite span with an elliptic circulation distribution:

Consider 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 information

ν δ - 1 -

ν 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 information

Introduction to Aerospace Engineering

Introduction 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 information

AE 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 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 information

The Importance of drag

The Importance of drag Drag Computation The Importance of drag Its effects on aircraft performances On the Concorde, one count drag increase (ΔC D =.0001) requires two passengers, out of the 90 ~ 100 passenger capacity, be taken

More information

The E80 Wind Tunnel Experiment the experience will blow you away. by Professor Duron Spring 2012

The E80 Wind Tunnel Experiment the experience will blow you away. by Professor Duron Spring 2012 The E80 Wind Tunnel Experiment the experience will blow you away by Professor Duron Spring 2012 Objectives To familiarize the student with the basic operation and instrumentation of the HMC wind tunnel

More information

Transonic Aerodynamics Wind Tunnel Testing Considerations. W.H. Mason Configuration Aerodynamics Class

Transonic Aerodynamics Wind Tunnel Testing Considerations. W.H. Mason Configuration Aerodynamics Class Transonic Aerodynamics Wind Tunnel Testing Considerations W.H. Mason Configuration Aerodynamics Class Transonic Aerodynamics History Pre WWII propeller tip speeds limited airplane speed Props did encounter

More information

SPC Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30

SPC Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30 SPC 307 - Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30 1. The maximum velocity at which an aircraft can cruise occurs when the thrust available with the engines operating with the

More information

Drag (2) Induced Drag Friction Drag Form Drag Wave Drag

Drag (2) Induced Drag Friction Drag Form Drag Wave Drag Drag () Induced Drag Friction Drag Form Drag Wave Drag Outline Nomenclature and Concepts Farfield Drag Analysis Induced Drag Multiple Lifting Surfaces Zero Lift Drag :Friction and Form Drag Supersonic

More information

Study of Preliminary Configuration Design of F-35 using simple CFD

Study of Preliminary Configuration Design of F-35 using simple CFD Study of Preliminary Configuration Design of F-35 using simple CFD http://www.aerospaceweb.org/aircraft/research/x35/pics.shtml David Hall Sangeon Chun David Andrews Center of Gravity Estimation.5873 Conventional

More information

Chapter 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. 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 information

Wings and Bodies in Compressible Flows

Wings and Bodies in Compressible Flows Wings and Bodies in Compressible Flows Prandtl-Glauert-Goethert Transformation Potential equation: 1 If we choose and Laplace eqn. The transformation has stretched the x co-ordinate by 2 Values of at corresponding

More information

Given a stream function for a cylinder in a uniform flow with circulation: a) Sketch the flow pattern in terms of streamlines.

Given a stream function for a cylinder in a uniform flow with circulation: a) Sketch the flow pattern in terms of streamlines. Question Given a stream function for a cylinder in a uniform flow with circulation: R Γ r ψ = U r sinθ + ln r π R a) Sketch the flow pattern in terms of streamlines. b) Derive an expression for the angular

More information

Masters in Mechanical Engineering Aerodynamics 1 st Semester 2015/16

Masters in Mechanical Engineering Aerodynamics 1 st Semester 2015/16 Masters in Mechanical Engineering Aerodynamics st Semester 05/6 Exam st season, 8 January 06 Name : Time : 8:30 Number: Duration : 3 hours st Part : No textbooks/notes allowed nd Part : Textbooks allowed

More information

Basic Low Speed Aerodynamics

Basic Low Speed Aerodynamics Basic Low Speed Aerodynamics Introduction I thought a discussion of basic low speed aerodynamics might be of interest for some of our EAA Chapter members so I prepared a series of notes that will address

More information

and K becoming functions of Mach number i.e.: (3.49)

and K becoming functions of Mach number i.e.: (3.49) Chapter 3 Lecture 11 Drag polar 6 Topics 3.3.4 Parabolic drag polar at high speeds 3.3.5 Guidelines for variations of C Do and K for subsonic jet transport airplanes 3.3.6 Variations of C Do and K for

More information

F-35: A case study. Eugene Heim Leifur Thor Leifsson Evan Neblett. AOE 4124 Configuration Aerodynamics Virginia Tech April 2003

F-35: A case study. Eugene Heim Leifur Thor Leifsson Evan Neblett. AOE 4124 Configuration Aerodynamics Virginia Tech April 2003 F-35: A case study Eugene Heim Leifur Thor Leifsson Evan Neblett AOE 4124 Configuration Aerodynamics Virginia Tech April 2003 Course: AOE 4124 Configuration Aerodynamics Project: A case study of the F-35

More information

Flight 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 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 information

PEMP ACD2501. M.S. Ramaiah School of Advanced Studies, Bengaluru

PEMP ACD2501. M.S. Ramaiah School of Advanced Studies, Bengaluru Aircraft Aerodynamics Session delivered by: Mr. Ramjan Pathan 1 Session Objectives At the end of this session students would have understood Basics of Fluid Mechanics Definition of fluid, Fluid flow applications

More information

PRINCIPLES OF FLIGHT

PRINCIPLES 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 information

AE 2020: Low Speed Aerodynamics. I. Introductory Remarks Read chapter 1 of Fundamentals of Aerodynamics by John D. Anderson

AE 2020: Low Speed Aerodynamics. I. Introductory Remarks Read chapter 1 of Fundamentals of Aerodynamics by John D. Anderson AE 2020: Low Speed Aerodynamics I. Introductory Remarks Read chapter 1 of Fundamentals of Aerodynamics by John D. Anderson Text Book Anderson, Fundamentals of Aerodynamics, 4th Edition, McGraw-Hill, Inc.

More information

Missile Interceptor EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P Ryan Donnan, Herman Ryals

Missile 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

Random Problems. Problem 1 (30 pts)

Random Problems. Problem 1 (30 pts) Random Problems Problem (3 pts) An untwisted wing with an elliptical planform has an aspect ratio of 6 and a span of m. The wing loading (defined as the lift per unit area of the wing) is 9N/m when flying

More information

The polar for uncambered and cambered airfoils. The angel of attack α

The polar for uncambered and cambered airfoils. The angel of attack α 13-1 13 Drag Prediction 13.1 Drag Polar In Section under Step 14 it was a requirement that the flight performance has to be checked to complete the aircraft design process. This is only possible if the

More information

AERO-STRUCTURAL MDO OF A SPAR-TANK-TYPE WING FOR AIRCRAFT CONCEPTUAL DESIGN

AERO-STRUCTURAL MDO OF A SPAR-TANK-TYPE WING FOR AIRCRAFT CONCEPTUAL DESIGN 1 26th INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AERO-STRUCTURAL MDO OF A SPAR-TANK-TYPE WING FOR AIRCRAFT CONCEPTUAL DESIGN Paulo R. Caixeta Jr., Álvaro M. Abdalla, Flávio D. Marques, Fernando

More information

Blade Element Momentum Theory

Blade Element Momentum Theory Blade Element Theory has a number of assumptions. The biggest (and worst) assumption is that the inflow is uniform. In reality, the inflow is non-uniform. It may be shown that uniform inflow yields the

More information

Mechanics of Flight. Warren F. Phillips. John Wiley & Sons, Inc. Professor Mechanical and Aerospace Engineering Utah State University WILEY

Mechanics of Flight. Warren F. Phillips. John Wiley & Sons, Inc. Professor Mechanical and Aerospace Engineering Utah State University WILEY Mechanics of Flight Warren F. Phillips Professor Mechanical and Aerospace Engineering Utah State University WILEY John Wiley & Sons, Inc. CONTENTS Preface Acknowledgments xi xiii 1. Overview of Aerodynamics

More information

Applied Fluid Mechanics

Applied Fluid Mechanics Applied Fluid Mechanics 1. The Nature of Fluid and the Study of Fluid Mechanics 2. Viscosity of Fluid 3. Pressure Measurement 4. Forces Due to Static Fluid 5. Buoyancy and Stability 6. Flow of Fluid and

More information

A Study of Transonic Flow and Airfoils. Presented by: Huiliang Lui 30 th April 2007

A Study of Transonic Flow and Airfoils. Presented by: Huiliang Lui 30 th April 2007 A Study of Transonic Flow and Airfoils Presented by: Huiliang Lui 3 th April 7 Contents Background Aims Theory Conservation Laws Irrotational Flow Self-Similarity Characteristics Numerical Modeling Conclusion

More information

Performance. 5. More Aerodynamic Considerations

Performance. 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 information

In-Flight Lift-Drag Characteristics for a Forward-Swept Wing Aircraft (and Comparisions With Contemporary Aircraft)

In-Flight Lift-Drag Characteristics for a Forward-Swept Wing Aircraft (and Comparisions With Contemporary Aircraft) NASA Technical Paper 3414 December 1994 In-Flight Lift-Drag Characteristics for a Forward-Swept Wing Aircraft (and Comparisions With Contemporary Aircraft) Edwin J. Saltzman and John W. Hicks NASA Technical

More information

Aero-Propulsive-Elastic Modeling Using OpenVSP

Aero-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 information

Chapter 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, 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 information

Configuration Aerodynamics

Configuration 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 information

EFFECT OF ATMOSPHERIC ALTITUDE ON THE DRAG OF WING AT SUBSONIC AND SUPERSONIC SPEEDS

EFFECT OF ATMOSPHERIC ALTITUDE ON THE DRAG OF WING AT SUBSONIC AND SUPERSONIC SPEEDS Journal of Engineering Science and Technology 6 th EURECA 2016 Special Issue May (2017) 71-83 School of Engineering, Taylor s University EFFECT OF ATMOSPHERIC ALTITUDE ON THE DRAG OF WING AT SUBSONIC AND

More information

The Wright Stuff. Engineering Analysis. Aaron Lostutter Adam Nelessen Brandon Perez Zev Vallance Jacob Vincent. November 2012

The Wright Stuff. Engineering Analysis. Aaron Lostutter Adam Nelessen Brandon Perez Zev Vallance Jacob Vincent. November 2012 The Wright Stuff Engineering Analysis November 2012 Aaron Lostutter Adam Nelessen Brandon Perez Zev Vallance Jacob Vincent 1 Agenda Static Analysis Aerodynamic Systems Propulsion Systems Structural & Material

More information

Aerodynamics 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 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 information

PERFORMANCE ANALYSIS OF A PISTON ENGINED AIRPLANE - PIPER CHEROKEE PA E.G.TULAPURKARA S.ANANTH TEJAS M. KULKARNI REPORT NO: AE TR

PERFORMANCE ANALYSIS OF A PISTON ENGINED AIRPLANE - PIPER CHEROKEE PA E.G.TULAPURKARA S.ANANTH TEJAS M. KULKARNI REPORT NO: AE TR Appendix - A PERFORMANCE ANALYSIS OF A PISTON ENGINED AIRPLANE - PIPER CHEROKEE PA-28-180 E.G.TULAPURKARA S.ANANTH TEJAS M. KULKARNI REPORT NO: AE TR 2007-1 FEBRUARY 2007 Performance Analysis of a piston

More information

Introduction to Flight

Introduction 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 information

344 JAXA Special Publication JAXA-SP E 2. Prediction by the CFD Approach 2.1 Numerical Procedure The plane shape of the thin delta wing of the r

344 JAXA Special Publication JAXA-SP E 2. Prediction by the CFD Approach 2.1 Numerical Procedure The plane shape of the thin delta wing of the r 5th Symposium on Integrating CFD and Experiments in Aerodynamics (Integration 2012) 343 Aerodynamic Characteristics of a Delta Wing with Arc Camber for Mars Exploration Takao Unoguchi,* 1 Shogo Aoyama,*

More information

DEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum

DEPARTMENT 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 information

Nose Cone & Fin Optimization

Nose Cone & Fin Optimization Nose Cone & Fin Optimization Tripoli Minnesota Gary Stroick January 2011 Purpose Focus is on drag optimization to maximize rocket performance! Copyright 2011 by Off We Go Rocketry 2 Agenda Definitions

More information

Supersonic Aerodynamics. Methods and Applications

Supersonic Aerodynamics. Methods and Applications Supersonic Aerodynamics Methods and Applications Outline Introduction to Supersonic Flow Governing Equations Numerical Methods Aerodynamic Design Applications Introduction to Supersonic Flow What does

More information

AA 242B/ ME 242B: Mechanical Vibrations (Spring 2016)

AA 242B/ ME 242B: Mechanical Vibrations (Spring 2016) AA 242B/ ME 242B: Mechanical Vibrations (Spring 2016) Homework #2 Due April 17, 2016 This homework focuses on developing a simplified analytical model of the longitudinal dynamics of an aircraft during

More information

Induced Drag and High-Speed Aerodynamics Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018

Induced Drag and High-Speed Aerodynamics Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018 Induced Drag and High-Speed Aerodynamics Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018 Drag-due-to-lift and effects of wing planform Effect of angle of attack on lift and drag coefficients Mach

More information

AEROSPACE ENGINEERING DEPARTMENT. Second Year - Second Term ( ) Fluid Mechanics & Gas Dynamics

AEROSPACE ENGINEERING DEPARTMENT. Second Year - Second Term ( ) Fluid Mechanics & Gas Dynamics AEROSPACE ENGINEERING DEPARTMENT Second Year - Second Term (2008-2009) Fluid Mechanics & Gas Dynamics Similitude,Dimensional Analysis &Modeling (1) [7.2R*] Some common variables in fluid mechanics include:

More information

Aerodynamics. Basic Aerodynamics. Continuity equation (mass conserved) Some thermodynamics. Energy equation (energy conserved)

Aerodynamics. Basic Aerodynamics. Continuity equation (mass conserved) Some thermodynamics. Energy equation (energy conserved) Flow with no friction (inviscid) Aerodynamics Basic Aerodynamics Continuity equation (mass conserved) Flow with friction (viscous) Momentum equation (F = ma) 1. Euler s equation 2. Bernoulli s equation

More information

Figure 1 UAV Geometry Base Case Design

Figure 1 UAV Geometry Base Case Design Unmanned Aerial Vehicle Design Endurance Optimization for Surveillance Missions ME 555 Design Optimization Progress Report Britton Bush, Jonathon Gold, and Erik Hand University of Michigan, Ann Arbor MI

More information

THE EFFECT OF WING GEOMETRY ON LIFT AT SUPERSONIC SPEEDS

THE EFFECT OF WING GEOMETRY ON LIFT AT SUPERSONIC SPEEDS Journal of Engineering Science and Technology EURECA 2013 Special Issue August (2014) 16-27 School of Engineering, Taylor s University THE EFFECT OF WING GEOMETRY ON LIFT AT SUPERSONIC SPEEDS ABDULKAREEM

More information

Fundamentals of Aerodynamics

Fundamentals 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 information

Q. 1 Q. 25 carry one mark each.

Q. 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 information

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.

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. 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 information

University 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 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 information

Study. Aerodynamics. Small UAV. AVL Software

Study. Aerodynamics. Small UAV. AVL Software Study of the Aerodynamics of a Small UAV using AVL Software Prepared For: Prof. Luis Bernal Prepared By: Paul Dorman April 24, 2006 Table of Contents Introduction.1 Aerodynamic Data...2 Flight Assessment..

More information

Fundamentals of Aerodynamits

Fundamentals of Aerodynamits Fundamentals of Aerodynamits Fifth Edition in SI Units John D. Anderson, Jr. Curator of Aerodynamics National Air and Space Museum Smithsonian Institution and Professor Emeritus University of Maryland

More information

Department of Energy Sciences, LTH

Department of Energy Sciences, LTH Department of Energy Sciences, LTH MMV11 Fluid Mechanics LABORATION 1 Flow Around Bodies OBJECTIVES (1) To understand how body shape and surface finish influence the flow-related forces () To understand

More information

Introduction to Aeronautics

Introduction to Aeronautics Introduction to Aeronautics ARO 101 Sections 03 & 04 Sep 30, 2015 thru Dec 9, 2015 Instructor: Raymond A. Hudson Week #8 Lecture Material 1 Topics For Week #8 Airfoil Geometry & Nomenclature Identify the

More information

The Fighter of the 21 st Century. Presented By Michael Weisman Configuration Aerodynamics 4/23/01

The Fighter of the 21 st Century. Presented By Michael Weisman Configuration Aerodynamics 4/23/01 The Fighter of the 21 st Century Presented By Michael Weisman Configuration Aerodynamics 4/23/01 1 Joint Strike Fighter (JSF) Program Its purpose is to develop and field an affordable and highly common

More information

Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics. Erik D. Olson. NASA Langley Research Center, Hampton, VA 23681

Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics. Erik D. Olson. NASA Langley Research Center, Hampton, VA 23681 Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics Erik D. Olson NASA Langley Research Center, Hampton, VA 23681 This paper lays out a comprehensive methodology for computing a

More information

Figure 3.71 example of spanwise loading due to aileron deflection.

Figure 3.71 example of spanwise loading due to aileron deflection. 3.7 ILERON DESIGN 3.7.1 Introduction It s very important for preliminary design to analyze the roll and turn performances of the aircraft, paying attention on its use and category. the system used for

More information

Wind-Tunnel Investigation of Aerodynamic Efficiency of Three Planar Elliptical Wings With Curvature of Quarter-Chord Line

Wind-Tunnel Investigation of Aerodynamic Efficiency of Three Planar Elliptical Wings With Curvature of Quarter-Chord Line NASA Technical Paper 3359 October 1993 Wind-Tunnel Investigation of Aerodynamic Efficiency of Three Planar Elliptical Wings With Curvature of Quarter-Chord Line Raymond E. Mineck and Paul M. H. W. Vijgen

More information

Mathematical Techniques for Pre-conceptual Design

Mathematical Techniques for Pre-conceptual Design Mathematical Techniques for Pre-conceptual Design Mathematical Modeling in Industry XI IMA University of Minnesota Mentor: John Hoffman, Lockheed Martin Tactical Systems Michael Case 1, Jeff Haack 2, MoonChang

More information

Wall treatments and wall functions

Wall treatments and wall functions Wall treatments and wall functions A wall treatment is the set of near-wall modelling assumptions for each turbulence model. Three types of wall treatment are provided in FLUENT, although all three might

More information

1. Fluid Dynamics Around Airfoils

1. 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 information

Sample question paper Model answers * AE 1301 Flight dynamics B.E./B.Tech Degree examination, November / December Anna University.

Sample question paper Model answers * AE 1301 Flight dynamics B.E./B.Tech Degree examination, November / December Anna University. Sample question paper Model answers * AE 1301 Flight dynamics B.E./B.Tech Degree examination, November / December 006. Anna University. Time: 3 hours Answer ALL questions Part A- (10 x = 0 marks) Maximum:

More information

AE Stability and Control of Aerospace Vehicles

AE 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 information

Stability and Control Some Characteristics of Lifting Surfaces, and Pitch-Moments

Stability 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 information

9.4 Miscellaneous topics flight limitations, operating envelop and V-n diagram Flight limitations Operating envelop 9.4.

9.4 Miscellaneous topics flight limitations, operating envelop and V-n diagram Flight limitations Operating envelop 9.4. Chapter 9 Lecture 31 Performance analysis V Manoeuvres 4 Topics 9.4 Miscellaneous topics flight limitations, operating envelop and V-n diagram 9.4.1 Flight limitations 9.4.2 Operating envelop 9.4.3 V-n

More information

Bluff Body, Viscous Flow Characteristics ( Immersed Bodies)

Bluff Body, Viscous Flow Characteristics ( Immersed Bodies) Bluff Body, Viscous Flow Characteristics ( Immersed Bodies) In general, a body immersed in a flow will experience both externally applied forces and moments as a result of the flow about its external surfaces.

More information

Brenda M. Kulfan, John E. Bussoletti, and Craig L. Hilmes Boeing Commercial Airplane Group, Seattle, Washington, 98124

Brenda M. Kulfan, John E. Bussoletti, and Craig L. Hilmes Boeing Commercial Airplane Group, Seattle, Washington, 98124 AIAA--2007-0684 Pressures and Drag Characteristics of Bodies of Revolution at Near Sonic Speeds Including the Effects of Viscosity and Wind Tunnel Walls Brenda M. Kulfan, John E. Bussoletti, and Craig

More information

Development of a Wave Drag Prediction Tool for the Conceptual Design Phase

Development of a Wave Drag Prediction Tool for the Conceptual Design Phase Master of Science Thesis Development of a Wave Drag Prediction Tool for the Conceptual Design Phase July 14th, 15 Faculty of Aerospace Engineering - Delft University of Technology J. Vargas Development

More information

Introduction to Aerospace Engineering

Introduction to Aerospace Engineering Introduction to Aerospace Engineering Lecture slides Challenge the future 3-0-0 Introduction to Aerospace Engineering Aerodynamics 5 & 6 Prof. H. Bijl ir. N. Timmer Delft University of Technology 5. Compressibility

More information

Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 2012/13

Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 2012/13 Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 212/13 Exam 2ª época, 2 February 213 Name : Time : 8: Number: Duration : 3 hours 1 st Part : No textbooks/notes allowed 2 nd Part :

More information

Compressible Potential Flow: The Full Potential Equation. Copyright 2009 Narayanan Komerath

Compressible 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 information

Applications of adjoint based shape optimization to the design of low drag airplane wings, including wings to support natural laminar flow

Applications of adjoint based shape optimization to the design of low drag airplane wings, including wings to support natural laminar flow Applications of adjoint based shape optimization to the design of low drag airplane wings, including wings to support natural laminar flow Antony Jameson and Kui Ou Aeronautics & Astronautics Department,

More information

Introduction to Aerospace Engineering

Introduction 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 information

Lecture 7 Boundary Layer

Lecture 7 Boundary Layer SPC 307 Introduction to Aerodynamics Lecture 7 Boundary Layer April 9, 2017 Sep. 18, 2016 1 Character of the steady, viscous flow past a flat plate parallel to the upstream velocity Inertia force = ma

More information

AIRFRAME NOISE MODELING APPROPRIATE FOR MULTIDISCIPLINARY DESIGN AND OPTIMIZATION

AIRFRAME NOISE MODELING APPROPRIATE FOR MULTIDISCIPLINARY DESIGN AND OPTIMIZATION AIRFRAME NOISE MODELING APPROPRIATE FOR MULTIDISCIPLINARY DESIGN AND OPTIMIZATION AIAA-2004-0689 Serhat Hosder, Joseph A. Schetz, Bernard Grossman and William H. Mason Virginia Tech Work sponsored by NASA

More information

Introduction to Flight Dynamics

Introduction 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 information

Coupled Fluid and Heat Flow Analysis Around NACA Aerofoil Profiles at Various Mach Numbers

Coupled Fluid and Heat Flow Analysis Around NACA Aerofoil Profiles at Various Mach Numbers International Journal of Engineering Research and Technology. ISSN 0974-3154 Volume 6, Number 2 (2013), pp. 249-258 International Research Publication House http://www.irphouse.com Coupled Fluid and Heat

More information

List of symbols. Latin symbols. Symbol Property Unit

List of symbols. Latin symbols. Symbol Property Unit Abstract Aircraft icing continues to be a threat for modern day aircraft. Icing occurs when supercooled large droplets (SLD s) impinge on the body of the aircraft. These droplets can bounce off, freeze

More information

Lecture-4. Flow Past Immersed Bodies

Lecture-4. Flow Past Immersed Bodies Lecture-4 Flow Past Immersed Bodies Learning objectives After completing this lecture, you should be able to: Identify and discuss the features of external flow Explain the fundamental characteristics

More information

Wing geometric parameter studies of a box wing aircraft configuration for subsonic flight

Wing geometric parameter studies of a box wing aircraft configuration for subsonic flight DOI:.139/EUCASS17-7 7 TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Wing geometric parameter studies of a box wing aircraft configuration for subsonic flight Fábio Cruz Ribeiro*, Adson

More information

X-31 Vector Aircraft, Low Speed Stability & Control, Comparisons of Wind Tunnel Data & Theory (Focus on Linear & Panel Codes)

X-31 Vector Aircraft, Low Speed Stability & Control, Comparisons of Wind Tunnel Data & Theory (Focus on Linear & Panel Codes) 39th AIAA Fluid Dynamics Conference 22-25 June 2009, San Antonio, Texas AIAA 2009-3898 27 th AIAA Applied Aerodynamics Conference, 22-25 June. 2009, San Antonio, TX, USA X-31 Vector Aircraft, Low Speed

More information