Jet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati
|
|
- Kenneth Burke
- 6 years ago
- Views:
Transcription
1 Lecture-17 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1
2 Lift: is used to support the weight of the aircraft Lift and Drag Drag: that directly opposes the motion of the aircraft 2
3 In straight and Level Flight, Lift = Weight and Thrust = Drag 3
4 4
5 5
6 Airfoil Geometry α = Angle of Attack c = chord length t/c = thickness ratio =max. thickness/c camber ratio = max. camber/c 6
7 Evolution of Airfoils Airfoils Types Early Designs - Designers mistakenly believed that these airfoils with sharp leading edges will have low drag. In practice, they stalled quickly, and generated considerable drag. 7
8 Lift Equation L = C L V 2 ρ/2 S If the angle of attack and other factors remain constant and airspeed is doubled, lift will be four times greater. 8
9 Ways of Controlling Lift Increase airspeed Change the angle of attack Change the shape of the airfoil Change the total area of the wings 9
10 Drag Parasite Drag (Profile Drag) Induced Drag Form Drag (Pressure Drag) Skin Friction Drag Wave Drag Interference Drag Form Drag - Drag due to the shape of the body Skin Friction Drag - Drag due to the friction between the surface and the flow. Interference Drag - created when the airflow around one part of the airplane interacts with the airflow around another. 10
11 Parasite Drag Reduction By proper design and streamlining the shape. Avoiding Protrusions on the surface. Retracting landing gears. 11
12 Parasite Drag is simply Skin Friction Drag+ Form Drag + Interference Drag + Wave Drag 12
13 Supersonic Wave Drag For a given airfoil or wing or aircraft, as the Mach Number is increased, the drag begins to increase above a free-stream Mach number of 0.8 or so due to shock waves that form around the configuration. 13
14 Shock waves 14
15 How can shock waves be minimized? Use wing sweep. Use supercritical airfoils, which keep the flow velocity over the airfoil and the local Mach number from exceeding Mach 1.1 or so. 15
16 How can shock waves be minimized? Use sweep. 0.8cos30 30 sweep M=
17 Lift and Drag 17
18 Induced Drag For a lifting wing, the air pressure on the top of the wing is lower than the pressure below the wing. The lines marking the center of the vortices are shown as blue vortex lines leading from the wing tips. 18
19 Boeing 727 test airplane (NASA) 19
20 The wing tip vortices produce a downwash of air behind the wing which is very strong near the wing tips and decreases toward the wing root. Downwash TOP SURFACE (relative low pressure) (relative high pressure) BOTTOM SURFACE 20
21 21
22 Induced Drag 22
23 Component of R 1 (parallel to V ) = Drag D 1 (due to skin friction and pressure drag due to separation). R = actual aerodynamic force including the effect of tip vortices. Component R (parallel to V ) is the actual Drag force D. D = D D i 1 23
24 Origin of Induced Drag Geometric angle of attack = angle between the chord line and flow direction However, local flow gets deflected downward by α i due to downwash. This angle is known as induced angle of attack (difference between local flow direction and freestream direction). α = α α eff i 24
25 D = Lsinα i Values of α I are generally small, and hence sinα i = α i Threfore D = Lα i, i i 25
26 Lift & downwash distributions The lift per unit span may vary as a function of distance along the wing because Chord varies along the length of the wing Each airfoil section is at a different geometric angle of attack (Twisted) From incompressible flow theory CL αi = π AR 26
27 For all wings, C D L i = Lαi = L AR π 1 2 C D L i = Lαi = CL ρv S 2 π AR 2 Di C = L 1 2 ρv S π AR 2 2 C C L Di = π AR 2 C C L Di = π ear where, e= span efficiency factor 27
28 For elliptical planform e=1 Lift Per Unit Span -b/2 +b/2 For other planforms e < 1 Therefore, CD i is minimum for elliptical planform 28
29 Total Drag Total Drag = Parasite Drag + Induced Drag D = D + D P C D 2 ρ 2 V S = CD ρ P 2 V S + CD ρ i 2 V S C = C + C D DP Di i 29
30 At High Values of α Wings Stall 30
31 Increasing the Angle of Attack to the Stall Point The above picture shows a normal airfoil during a typical cruise profile. The angle of attack is small and the airflow over the wing is smooth, producing lift. No stall condition exists. In the left picture, the angle of attack has been increased and is now closer to/approaching the critical angle of attack. Airflow above the wing is becoming uneven. However, the angle is still less than the critical angle, so lift is still being produced by the wing. No stall condition exists. 31
32 Stalled Wing In the picture above, the wing has now exceeded its critical angle of attack. The uneven airflow over the top of the wing has broken into a swirling air mass that can not produce lift. The wing (airfoil) is "stalled". 32
33 33
34 Leading Edge Slats Help avoid stall near the leading edge 34
35 Lift Augmentation Devices Slat - It is placed in front of the airfoil to help increase the momentum of the boundary layer fluid. High energy air from the bottom side of the airfoil flows through the gap to the upper side, energizes slow speed molecules, and keeps the flow from stalling Thus it delays the separation and enhance the lift. Flap- It is placed at the rear of the wing it allows higher momentum fluid to replace the weaker fluid in the tail of the wing. Thus it avoid separation. It also increases the drag. 35
36 Achieving High Lift 36
37 Effect of High-Lift Devices Effect of leading edge devices on lift curve (Jenkinson). 37
38 38
39 39
40 One form of flaps, called Fowler flaps increase the chord length as the flap is deployed. 40
41 Summary Lift and Drag, Airfoil Terminology, Types of Drag, Downwash, Induced Drag, Flaps and Slats, Types of Flaps 41
42 References & Web Resources 1. Anderson, J. D. Jr., (2000), Introduction to Flight, 4 th Edition, McGraw Hill. 2. Anderson, J. D. Jr., (1999), Aircraft Performance and Design, McGraw Hill. 3. Shevell, R. S., (1989), Fundamentals of Flight, Pearson Education. 4. Clancy, L. J., (1996), Aerodynamics, Himalayan Books
ROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)
Unit D-1: Aerodynamics of 3-D Wings Page 1 of 5 AE301 Aerodynamics I UNIT D: Applied Aerodynamics ROAD MAP... D-1: Aerodynamics of 3-D Wings D-: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics
More informationAE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.
Aerodynamics: Introduction Aerodynamics deals with the motion of objects in air. These objects can be airplanes, missiles or road vehicles. The Table below summarizes the aspects of vehicle performance
More informationThe effect of back spin on a table tennis ball moving in a viscous fluid.
How can planes fly? The phenomenon of lift can be produced in an ideal (non-viscous) fluid by the addition of a free vortex (circulation) around a cylinder in a rectilinear flow stream. This is known as
More informationWelcome to Aerospace Engineering
Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 4 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route
More informationDEFINITIONS. Aerofoil
Aerofoil DEFINITIONS An aerofoil is a device designed to produce more lift (or thrust) than drag when air flows over it. Angle of Attack This is the angle between the chord line of the aerofoil and the
More informationHomework Exercise to prepare for Class #2.
Homework Exercise to prepare for Class #2. Answer these on notebook paper then correct or improve your answers (using another color) by referring to the answer sheet. 1. Identify the major components depicted
More informationLift for a Finite Wing. all real wings are finite in span (airfoils are considered as infinite in the span)
Lift for a Finite Wing all real wings are finite in span (airfoils are considered as infinite in the span) The lift coefficient differs from that of an airfoil because there are strong vortices produced
More informationChapter 5 Wing design - selection of wing parameters - 3 Lecture 21 Topics
Chapter 5 Wing design - selection of wing parameters - 3 Lecture 21 Topics 5.3.2 Choice of sweep ( ) 5.3.3 Choice of taper ratio ( λ ) 5.3.4 Choice of twist ( ε ) 5.3.5 Wing incidence(i w ) 5.3.6 Choice
More informationIncompressible Flow over Airfoils
Road map for Chap. 4 Incompressible Flow over Airfoils Aerodynamics 2015 fall - 1 - < 4.1 Introduction > Incompressible Flow over Airfoils Incompressible flow over airfoils Prandtl (20C 초 ) Airfoil (2D)
More informationBasic Fluid Mechanics
Basic Fluid Mechanics Chapter 7B: Forces on Submerged Bodies 7/26/2018 C7B: Forces on Submerged Bodies 1 Forces on Submerged Bodies Lift and Drag are forces exerted on an immersed body by the surrounding
More informationPreliminary Analysis of Drag Reduction for The Boeing
Preliminary Analysis of Drag Reduction for The Boeing 747-400 By: Chuck Dixon, Chief Scientist, Vortex Control Technologies LLC 07. 31. 2012 Potential for Airflow Separation That Can Be Reduced By Vortex
More informationInvestigation on 3-D Wing of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent
Investigation on 3-D of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent Rohit Jain 1, Mr. Sandeep Jain 2, Mr. Lokesh Bajpai 3 1PG Student, 2 Associate Professor, 3 Professor & Head 1 2 3
More informationLow Speed Wind Tunnel Wing Performance
Low Speed Wind Tunnel Wing Performance ARO 101L Introduction to Aeronautics Section 01 Group 13 20 November 2015 Aerospace Engineering Department California Polytechnic University, Pomona Team Leader:
More informationEffect of Co-Flow Jet over an Airfoil: Numerical Approach
Contemporary Engineering Sciences, Vol. 7, 2014, no. 17, 845-851 HIKARI Ltd, www.m-hikari.com http://dx.doi.org/10.12988/ces.2014.4655 Effect of Co-Flow Jet over an Airfoil: Numerical Approach Md. Riajun
More informationUncontrolled copy not subject to amendment. Principles of Flight
Uncontrolled copy not subject to amendment Principles of Flight Principles of Flight Learning Outcome 1: Know the principles of lift, weight, thrust and drag and how a balance of forces affects an aeroplane
More informationAero Club. Introduction to Flight
Aero Club Presents Introduction to RC Modeling Module 1 Introduction to Flight Centre For Innovation IIT Madras Page2 Table of Contents Introduction:... 3 How planes fly How is lift generated?... 3 Forces
More informationPrinciples of glider flight
Principles of glider flight [ Lecture 1: Lift, drag & glide performance ] Richard Lancaster Email: Richard@RJPLancaster.net Twitter: @RJPLancaster ASK-21 illustrations Copyright 1983 Alexander Schleicher
More informationWing-Body Combinations
Wing-Body Combinations even a pencil at an angle of attack will generate lift, albeit small. Hence, lift is produced by the fuselage of an airplane as well as the wing. The mating of a wing with a fuselage
More informationBUILD AND TEST A WIND TUNNEL
LAUNCHING INTO AVIATION 9 2018 Aircraft Owners and Pilots Association. All Rights Reserved. UNIT 2 SECTION D LESSON 2 PRESENTATION BUILD AND TEST A WIND TUNNEL LEARNING OBJECTIVES By the end of this lesson,
More informationAERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK SUPREETH NARASIMHAMURTHY GRADUATE STUDENT 1327291 Table of Contents 1) Introduction...1 2) Methodology.3 3) Results...5
More informationPRE-TEST Module 2 The Principles of Flight Units /60 points
PRE-TEST Module 2 The Principles of Flight Units 1-2-3.../60 points 1 Answer the following questions. (20 p.) moving the plane (4) upward / forward. Opposed to that is 1. What are the names of the four
More informationDIRECCION DE PERSONAL AERONAUTICO DPTO. DE INSTRUCCION PREGUNTAS Y OPCIONES POR TEMA
MT DIREION DE PERSONL ERONUTIO DPTO. DE INSTRUION PREGUNTS Y OPIONES POR TEM 1 TEM: 0292 FLT/DSP - (HP. 03) ERODYNMIS OD_PREG: PREG20084823 (8324) PREGUNT: When are inboard ailerons normally used? Low-speed
More informationIt should be noted that the symmetrical airfoil at zero lift has no pitching moment about the aerodynamic center because the upper and
NAVWEPS -81-8 and high power, the dynamic pressure in the shaded area can be much greater than the free stream and this causes considerably greater lift than at zero thrust. At high power conditions the
More informationA103 AERODYNAMIC PRINCIPLES
A103 AERODYNAMIC PRINCIPLES References: FAA-H-8083-25A, Pilot s Handbook of Aeronautical Knowledge, Chapter 3 (pgs 4-10) and Chapter 4 (pgs 1-39) OBJECTIVE: Students will understand the fundamental aerodynamic
More informationDrag Divergence and Wave Shock. A Path to Supersonic Flight Barriers
Drag Divergence and Wave Shock A Path to Supersonic Flight Barriers Mach Effects on Coefficient of Drag The Critical Mach Number is the velocity on the airfoil at which sonic flow is first acquired If
More informationAerodynamics Principles
Aerodynamics Principles Stage 1 Ground Lesson 3 Chapter 3 / Pages 2-18 3:00 Hrs Harold E. Calderon AGI, CFI, CFII, and MEI Lesson Objectives Become familiar with the four forces of flight, aerodynamic
More informationWHAT IS GLIDER? A light engineless aircraft designed to glide after being towed aloft or launched from a catapult.
GLIDER BASICS WHAT IS GLIDER? A light engineless aircraft designed to glide after being towed aloft or launched from a catapult. 2 PARTS OF GLIDER A glider can be divided into three main parts: a)fuselage
More informationC-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory
ROAD MAP... AE301 Aerodynamics I UNIT C: 2-D Airfoils C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory AE301 Aerodynamics I : List of Subjects
More informationAircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, Figures
Aircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012 Chapter 5 Wing Design Figures 1 Identify and prioritize wing design requirements (Performance, stability, producibility, operational
More informationAerodynamic Terms. Angle of attack is the angle between the relative wind and the wing chord line. [Figure 2-2] Leading edge. Upper camber.
Chapters 2 and 3 of the Pilot s Handbook of Aeronautical Knowledge (FAA-H-8083-25) apply to powered parachutes and are a prerequisite to reading this book. This chapter will focus on the aerodynamic fundamentals
More informationAerodynamic Analysis of Blended Winglet for Low Speed Aircraft
, July 1-3, 2015, London, U.K. Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft Pooja Pragati, Sudarsan Baskar Abstract This paper provides a practical design of a new concept of massive
More informationChapter 5 Wing design - selection of wing parameters - 4 Lecture 22 Topics
Chapter 5 Wing design - selection of wing parameters - Lecture Topics 5.3.9 Ailerons 5.3.0 Other aspects of wing design Example 5. 5.3.9 Ailerons The main purpose of the ailerons is to create rolling moment
More informationFUSELAGE. An aircraft s main body section that holds crew and passengers or cargo It is derived from the French word Fusele Spindle shaped
DAY 2 FUSELAGE FUSELAGE An aircraft s main body section that holds crew and passengers or cargo It is derived from the French word Fusele Spindle shaped FUSELAGE FUSELAGE ASSEMBLAGE TYPES OF FUSELAGE STRUCTURE
More informationTheory of Flight Aircraft Design and Construction. References: FTGU pages 9-14, 27
Theory of Flight 6.01 Aircraft Design and Construction References: FTGU pages 9-14, 27 Main Teaching Points Parts of an Airplane Aircraft Construction Landing Gear Standard Terminology Definition The airplane
More informationTheory of Flight Stalls. References: FTGU pages 18, 35-38
Theory of Flight 6.07 Stalls References: FTGU pages 18, 35-38 Review 1. What are the two main types of drag? 2. Is it possible to eliminate induced drag? Why or why not? 3. What is one way to increase
More informationDIRECCION DE PERSONAL AERONAUTICO DPTO. DE INSTRUCCION PREGUNTAS Y OPCIONES POR TEMA
MT DIREION DE PERSONL ERONUTIO DPTO. DE INSTRUION PREGUNTS Y OPIONES POR TEM 1 TEM: 0114 TP - (HP. 03) ERODYNMIS OD_PREG: PREG20078023 (8358) PREGUNT: What is the safest and most efficient takeoff and
More informationAircraft Stability and Performance 2nd Year, Aerospace Engineering. Dr. M. Turner
Aircraft Stability and Performance 2nd Year, Aerospace Engineering Dr. M. Turner Basic Info Timetable 15.00-16.00 Monday Physics LTA 16.00-17.00 Monday Physics LTA Exam 2 1 2 hour exam 6 questions 2 from
More informationAE Advanced Aircraft Design I
TU Delft Summary AE4240 - Advanced Aircraft Design I January 12, 2015 Contents 1 Design objectives 2 1.1 Conceptual Design..................................................................... 2 1.2 Preliminary
More informationAerodynamics of Winglet: A Computational Fluid Dynamics Study Using Fluent
Aerodynamics of : A Computational Fluid Dynamics Study Using Fluent Rohit Jain 1, Mr. Sandeep Jain, Mr. Lokesh Bajpai 1PG Student, Associate Professor, Professor & Head 1 Mechanical Engineering Department
More informationReduction of Skin Friction Drag in Wings by Employing Riblets
Reduction of Skin Friction Drag in Wings by Employing Riblets Kousik Kumaar. R 1 Assistant Professor Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Coimbatore, India
More informationThe Metric Glider. By Steven A. Bachmeyer. Aerospace Technology Education Series
The Metric Glider By Steven A. Bachmeyer Aerospace Technology Education Series 10002 Photographs and Illustrations The author wishes to acknowledge the following individuals and organizations for the photographs
More informationAerodynamics. A study guide on aerodynamics for the Piper Archer
Aerodynamics A study guide on aerodynamics for the Piper Archer Aerodynamics The purpose of this pilot briefing is to discuss the simple and complex aerodynamics of the Piper Archer. Please use the following
More informationFigure 1. Curtis 1911 model D type IV pusher
This material can be found in more detail in Understanding Flight 1 st and 2 nd editions by David Anderson and Scott Eberhardt, McGraw-Hill, 2001, and 2009 A Physical Description of Flight; Revisited David
More informationDetailed study 3.4 Topic Test Investigations: Flight
Name: Billanook College Detailed study 3.4 Topic Test Investigations: Flight Ivanhoe Girls Grammar School Questions 1 and 2 relate to the information shown in the diagram in Figure 1. z Question 1 y Figure
More information11-1. Horizontal tailplane sizing according to control requirement
11-1 11 Empennage izing In ection Empennage General Design, the areas of the horizontal and vertical tailplanes were calculated merely with the aid of tail volume coefficients. The tail lever arms were
More informationParasite Drag. by David F. Rogers Copyright c 2005 David F. Rogers. All rights reserved.
Parasite Drag by David F. Rogers http://www.nar-associates.com Copyright c 2005 David F. Rogers. All rights reserved. How many of you still have a Grimes rotating beacon on both the top and bottom of the
More informationCFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS
www.mechieprojects.com CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS PRESENTATION OUTLINE AIM INTRODUCTION LITERATURE SURVEY CFD ANALYSIS OF AEROFOIL RESULTS CONCLUSIONS www.mechieprojects.com
More informationAerodynamic Analysis of a Symmetric Aerofoil
214 IJEDR Volume 2, Issue 4 ISSN: 2321-9939 Aerodynamic Analysis of a Symmetric Aerofoil Narayan U Rathod Department of Mechanical Engineering, BMS college of Engineering, Bangalore, India Abstract - The
More informationEXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE Lemes, Rodrigo Cristian,
More informationInvestigation and Comparison of Airfoils
AENG 360 Aerodynamics Investigation and Comparison of Airfoils Rocie Benavent Chelseyann Bipat Brandon Gilyard Julian Marcon New York Institute of Technology Fall 2013 2 Executive Summary Airfoil design
More informationReynolds Number Effects on Leading Edge Vortices
Reynolds Number Effects on Leading Edge Vortices Taken From AIAA-2002-2839 Paper Reynolds Numbers Considerations for Supersonic Flight Brenda M. Kulfan 32nd AIAA Fluid Dynamics Conference and Exhibit St.
More informationAerodynamic Basics Larry Bogan - Jan 2002 version MECHANICS
Aerodynamic Basics Larry Bogan - Jan 2002 version MECHANICS Vectors Force, displacement, acceleration, and velocity Inertia and Velocity Inertia is a property of mass. (When there is no force on an object,
More informationNumerical Analysis of Wings for UAV based on High-Lift Airfoils
Numerical Analysis of Wings for UAV based on High-Lift Airfoils Sachin Srivastava Department of Aeronautical Engineering Malla Reddy College of Engineering & Technology, Hyderabad, Telangana, India Swetha
More informationIncompressible Flow over Airfoils
< 4.7 Classical Thin Airfoil Theory > The Symmetric Airfoil * Assumptions Incompressible Flow over Airfoils i) The camber line is one of the streamlines ii) Small maximum camber and thickness relative
More informationThe subsonic compressibility effect is added by replacing. with
Swept Wings The main function of a swept wing is to reduce wave drag at transonic and supersonic speeds. Consider a straight wing and a swept wing in a flow with a free-stream velocity V. Assume that the
More informationImproved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped Fuselage
International Journal of Scientific & Engineering Research Volume 4, Issue 1, January-213 1 Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped
More informationANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT
ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT P.Sethunathan 1, M.Niventhran 2, V.Siva 2, R.Sadhan Kumar 2 1 Asst.Professor, Department of Aeronautical Engineering,
More informationUncontrolled copy not subject to amendment. Principles of Flight
Uncontrolled copy not subject to amendment Principles of Flight Principles of Flight Learning Outcome 3: Know the principles of stalling Principles of Flight Revision Questions What effect does a Trailing
More informationSOARING AND GLIDING FLIGHT OF THE BLACK VULTURE
[ 280 ] SOARING AND GLIDING FLIGHT OF THE BLACK VULTURE BY B. G. NEWMAN* Department of Engineering, University of Cambridge {Received 10 September 1957) INTRODUCTION In 1950 Raspet published an interesting
More informationNo Description Direction Source 1. Thrust
AERODYNAMICS FORCES 1. WORKING TOGETHER Actually Lift Force is not the only force working on the aircraft, during aircraft moving through the air. There are several aerodynamics forces working together
More informationAERODYNAMIC ANALYSIS OF MULTI-WINGLETS FOR LOW SPEED AIRCRAFT
AERODYNAMIC ANALYSIS OF MULTI-WINGLETS FOR LOW SPEED AIRCRAFT Cosin, R., Catalano, F.M., Correa, L.G.N., Entz, R.M.U. Engineering School of São Carlos - University of São Paulo Keywords: multi-winglets,
More informationTwist Distributions for Swept Wings, Part 2
On the Wing... #162 Twist Distributions for Swept Wings, Part 2 Having defined and provided examples of lift distributions in Part 1, we now move on to describing the stalling patterns of untwisted and
More informationFlight Control Systems Introduction
Flight Control Systems Introduction Dr Slide 1 Flight Control System A Flight Control System (FCS) consists of the flight control surfaces, the respective cockpit controls, connecting linkage, and necessary
More informationIncompressible Potential Flow. Panel Methods (3)
Incompressible Potential Flow Panel Methods (3) Outline Some Potential Theory Derivation of the Integral Equation for the Potential Classic Panel Method Program PANEL Subsonic Airfoil Aerodynamics Issues
More informationII.E. Airplane Flight Controls
References: FAA-H-8083-3; FAA-8083-3-25 Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge of the elements related to
More informationJ. Szantyr Lecture No. 21 Aerodynamics of the lifting foils Lifting foils are important parts of many products of contemporary technology.
J. Szantyr Lecture No. 21 Aerodynamics of the lifting foils Lifting foils are important parts of many products of contemporary technology. < Helicopters Aircraft Gliders Sails > < Keels and rudders Hydrofoils
More informationComputational Analysis of Cavity Effect over Aircraft Wing
World Engineering & Applied Sciences Journal 8 (): 104-110, 017 ISSN 079-04 IDOSI Publications, 017 DOI: 10.589/idosi.weasj.017.104.110 Computational Analysis of Cavity Effect over Aircraft Wing 1 P. Booma
More informationEXPERIMENTAL ANALYSIS OF FLOW OVER SYMMETRICAL AEROFOIL Mayank Pawar 1, Zankhan Sonara 2 1,2
EXPERIMENTAL ANALYSIS OF FLOW OVER SYMMETRICAL AEROFOIL Mayank Pawar 1, Zankhan Sonara 2 1,2 Assistant Professor,Chandubhai S. Patel Institute of Technology, CHARUSAT, Changa, Gujarat, India Abstract The
More informationDesign and Analysis of Aircraft Winglets Using CFD
Design and Analysis of Aircraft Winglets Using CFD N. Krishnaveni M.Tech (CAAD) Department of Mechanical Engineering Gayatri Vidyaparishad College of Engineering (Autonomus) Visakhapatnam-530048 ABSTRACT
More informationLearn About. Quick Write
LESSON 2 The Physics of Flight Y Quick Write Octave Chanute s expertise in designing bridges gave him the know-how to tackle some big questions in aviation, such as the structure of biplane wings. What
More informationFlow Over Bodies: Drag and Lift
Fluid Mechanics (0905241) Flow Over Bodies: Drag and Lift Dr.-Eng. Zayed dal-hamamre 1 Content Overview Drag and Lift Flow Past Objects Boundary Layers Laminar Boundary Layers Transitional and Turbulent
More informationPASSIVE FLOW SEPARATION CONTROL BY STATIC EXTENDED TRAILING EDGE
Proceedings of the International Conference on Mechanical Engineering and Renewable Energy 25 (ICMERE25) 26 29 November, 25, Chittagong, Bangladesh ICMERE25-PI-232 PASSIVE FLOW SEPARATION CONTROL BY STATIC
More informationForces in Flight. to the drag force. Direction of Forces in Straight and Level Flight. Weight
Forces in Flight The flight of an airplane, a bird, or any other object involves four forces that may be measured and compared: lift, drag, thrust, and weight. As can be seen in the figure below for straight
More informationLearning Objectives 081 Principles of Flight
Learning Objectives 081 Principles of Flight Conventions for questions in subject 081. 1. The following standard conventions are used for certain mathematical symbols: * multiplication. > = greater than
More informationCASE STUDY FOR USE WITH SECTION B
GCE A level 135/01-B PHYSICS ASSESSMENT UNIT PH5 A.M. THURSDAY, 0 June 013 CASE STUDY FOR USE WITH SECTION B Examination copy To be given out at the start of the examination. The pre-release copy must
More informationUNCORRECTED PAGE PROOFS
CHAPTER 18 How do heavy things fly? Contents Flight the beginning Forces acting on an aircraft Moving through fluids The Equation of Continuity Fluid speed and pressure Aerofoil characteristics Newton
More informationPrinciples of Flight. Chapter 4. From the Library at Introduction. Structure of the Atmosphere
From the Library at www.uavgroundschool.com Chapter 4 Principles of Flight Introduction This chapter examines the fundamental physical laws governing the forces acting on an aircraft in flight, and what
More informationATPL Principles of Flight - deel 2
ATPL Principles of Flight - deel 2 1. If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less then wing span) A decrease B remain
More informationAnna University Regional office Tirunelveli
Effect of Tubercle Leading Edge Control Surface on the Performance of the Double Delta Wing Fighter Aircraft P Sharmila 1, S Rajakumar 2 1 P.G. Scholar, 2 Assistant Professor, Mechanical Department Anna
More informationCFD Analysis of Effect of Variation in Angle of Attack over NACA 2412 Airfoil through the Shear Stress Transport Turbulence Model
IJSRD - International Journal for Scientific Research & Development Vol. 5, Issue 02, 2017 ISSN (online): 2321-0613 CFD Analysis of Effect of Variation in Angle of Attack over NACA 2412 Airfoil through
More informationPOWERED FLIGHT HOVERING FLIGHT
Once a helicopter leaves the ground, it is acted upon by the four aerodynamic forces. In this chapter, we will examine these forces as they relate to flight maneuvers. POWERED FLIGHT In powered flight
More informationLAPL(A)/PPL(A) question bank FCL.215, FCL.120 Rev PRINCIPLES OF FLIGHT 080
PRINCIPLES OF FLIGHT 080 1 Density: Is unaffected by temperature change. Increases with altitude increase. Reduces with temperature reduction. Reduces with altitude increase. 2 The air pressure that acts
More informationPreliminary Design Review (PDR) Aerodynamics #2 AAE-451 Aircraft Design
Preliminary Design Review (PDR) Aerodynamics #2 AAE-451 Aircraft Design Aircraft Geometry (highlight any significant revisions since Aerodynamics PDR #1) Airfoil section for wing, vertical and horizontal
More informationExternal Tank- Drag Reduction Methods and Flow Analysis
External Tank- Drag Reduction Methods and Flow Analysis Shaik Mohammed Anis M.Tech Student, MLR Institute of Technology, Hyderabad, India. G. Parthasarathy Associate Professor, MLR Institute of Technology,
More informationBRONZE LECTURES. Slides on bayriver.co.uk/gliding
BRONZE LECTURES 2014 Slides on bayriver.co.uk/gliding 1 STUDY Lectures only meant to be a stimulus and provide an opportunity for questions EXAM paper is multi-choice with x sections. 2 READING BOOKS?
More informationThe Fly Higher Tutorial IV
The Fly Higher Tutorial IV THE SCIENCE OF FLIGHT In order for an aircraft to fly we must have two things: 1) Thrust 2) Lift Aerodynamics The Basics Representation of the balance of forces These act against
More informationCOMPUTER-AIDED DESIGN AND PERFORMANCE ANALYSIS OF HAWT BLADES
5 th International Advanced Technologies Symposium (IATS 09), May 13-15, 2009, Karabuk, Turkey COMPUTER-AIDED DESIGN AND PERFORMANCE ANALYSIS OF HAWT BLADES Emrah KULUNK a, * and Nadir YILMAZ b a, * New
More informationWINGLET CANT AND SWEEP ANGLES EFFECT ON AIRCRAFT WING PERFORMANCE
Proceedings of the 17 th Int. AMME Conference, 19-21 April, 216 258 Military Technical College Kobry El-Kobbah, Cairo, Egypt. 17 th International Conference on Applied Mechanics and Mechanical Engineering.
More informationVolume 2, Issue 5, May- 2015, Impact Factor: Structural Analysis of Formula One Racing Car
Structural Analysis of Formula One Racing Car Triya Nanalal Vadgama 1, Mr. Arpit Patel 2, Dr. Dipali Thakkar 3, Mr. Jignesh Vala 4 Department of Aeronautical Engineering, Sardar Vallabhbhai Patel Institute
More informationAerodynamics: The Wing Is the Thing
Page B1 Chapter Two Chapter Two Aerodynamics: The Wing Is the Thing The Wing Is the Thing May the Four Forces Be With You 1. [B1/3/2] The four forces acting on an airplane in flight are A. lift, weight,
More informationOBJECTIVE METHODOLOGY
SKMA394 Measurement of Pressure Distribution around an Airfoil NACA445 OBJECTIVE The objective of this experiment is to study about the pressure distribution around the surface of aerofoil NACA 445 starting
More informationAERODYNAMICS I LECTURE 7 SELECTED TOPICS IN THE LOW-SPEED AERODYNAMICS
LECTURE 7 SELECTED TOPICS IN THE LOW-SPEED AERODYNAMICS The sources of a graphical material used in this lecture are: [UA] D. McLean, Understanding Aerodynamics. Arguing from the Real Physics. Wiley, 2013.
More informationHIGH ALTITUDE AERODYNAMICS
HIGH ALTITUDE AERODYNAMICS CRITICAL ASPECTS OF MACH FLIGHT In recent years, a number of corporate jet airplanes have been involved in catastrophic loss of control during high-altitude/high-speed flight.
More informationXI.C. Power-Off Stalls
References: FAA-H-8083-3; POH/AFM Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge of stalls regarding aerodynamics,
More informationAirframes. Chapter 5: Wings & Tailplane
Airframes Chapter 5: Wings & Tailplane 1 2 Learning Objectives The purpose of this chapter is to discuss in more detail, 2 of the 4 major components, the Wing (or mainplane) and the Tailplane. By the end
More informationINTERFERENCE EFFECT AND FLOW PATTERN OF FOUR BIPLANE CONFIGURATIONS USING NACA 0024 PROFILE
Proceedings of the International Conference on Mechanical Engineering 211 (ICME211) 18-2 December 211, Dhaka, Bangladesh ICME11-FL-1 INTERFERENCE EFFECT AND FLOW PATTERN OF FOUR BIPLANE CONFIGURATIONS
More informationHoward Torode. Member of General Aviation Group and Chairman BGA Technical Committee
Efficient Light Aircraft Design Options from Gliding Howard Torode Member of General Aviation Group and Chairman BGA Technical Committee Presentation Aims Recognise the convergence of interest between
More informationScience of Flight. Introduction to Aerodynamics for the Science Student By Pat Morgan
Science of Flight Introduction to Aerodynamics for the Science Student By Pat Morgan Why does a Paper Airplane Fly? A paper airplane flies because of the scientific properties of gases, which make up our
More informationExploration Series. AIRPLANE Interactive Physics Simulation Page 01
AIRPLANE ------- Interactive Physics Simulation ------- Page 01 What makes an airplane "stall"? An airplane changes its state of motion thanks to an imbalance in the four main forces acting on it: lift,
More informationAerodynamic investigations on a wing in ground effect
Aerodynamic investigations on a wing in ground effect A summary of NLR activities in the Seabus-Hydaer programme W.B. de Wolf Nationaal Lucht- en Ruimtevaartlaboratorium National Aerospace Laboratory NLR
More information