Flow Over Bodies: Drag and Lift

Size: px
Start display at page:

Download "Flow Over Bodies: Drag and Lift"

Transcription

1 Fluid Mechanics ( ) 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 Boundary Layers Drag on Immersed Objects Lift on Immersed Objects 2

2 External Flows: Overview If a body is immersed in a flow, we call it an external flow. External flows involving air are typically termed aerodynamics. Some important external flows include airplanes, motor vehicles, and flow around buildings, under water submarine. In internal flows, the entire flow field is dominated by viscous effects, while In external flow, the viscous effects are confined to a portion of the flow field such as the boundary layers and wakes. When a fluid moves over a solid body, it exerts pressure forces normal to the surface and shear forces parallel to the surface along the outer surface of the body. The component of the resultant pressure and shear forces that acts in the flow direction is called the drag force (or just drag), and the component that acts normal to the flow direction is called the lift force (or just lift). 3 External Flows: Overview Often flow modeling is used to determine the flow fields in a wind tunnel or water tank. Fuel economy, speed, acceleration, maneuverability, stability, and control are directly related to the aerodynamic/hydrodynamic forces and moments. correct design Typical quantities of interest are lift and drag acting on these objects. The flow fields and geometries for most external flow problems are too complicated to be solved analytically, and thus we have to rely on correlations based on experimental data Such testing is done in wind tunnels 4

3 Example: Automobile Drag Development of the C w value for motor vehicles 5 External Flows: Overview Types of External Flows: Two-Dimensional: infinitely long and of constant cross- sectional size and shape the flow is normal to the body. the end effects are negligible Axisymmetric: formed by rotating their crosssectional shape about the axis of symmetry. Three-Dimensional: may or may not possess a line of symmetry. The bodies can be classified as streamlined or blunt, tends to block the flow, buildings. Streamlined object typically move more easily through a fluid, airfoils, racing cars. A fluid may exert forces and moments on a body in and about various directions The force a flowing fluid exerts on a body in the flow direction is called drag 6

4 External Flows: Drag and Lift When any body moves through a fluid, an interaction between the body and the fluid occurs; forces at the fluid body bd it interface. Normal stresses due to the pressure, Pressure Distributions around an object lead to lift and drag. Shear Stresses on the surface also lead to lift and drag. Drag: Aligned with the Flow Lift: Normal to the Flow 7 Example: Automobile Drag Scion XB Porsche 911 C D = 1.0, A = 25 ft 2, C D A = 25ft 2 C D = 0.28, A = 10 ft 2, C D A = 2.8ft 2 Drag force F D =1/2 V 2 (C D A) will be ~ 10 times larger for Scion XB Source is large C D and large projected area Power consumption P = F V=1/2 V D 3 (C D A) for both scales with V 3! 8

5 Example Air at standard conditions flows past a flat plate as is indicated. In case a the plate is parallel to the upstream flow, and in case b it is perpendicular to the upstream flow. If the pressure and shear stress distributions on the surface are as indicated, obtained either by experiment or theory, determine the lift and drag on the plate. 9 Example Cont. 10

6 Example Cont. The friction drag is zero for a flat surface normal to flow, and maximum for a flat surface parallel to flow The pressure drag is proportional to the frontal area and to the difference bt between the pressures acting on the front and back of the immersed body. 11 External Flows: Flow Past Objects The fluid velocity ranges from zero at the surface (the no-slip condition) to the freestream value away from the surface The character of the flow field is a function of the shape of the body size, orientation,s peed, and fluid properties. Low Reynolds, Number: Re = 0.1 strong viscous effects, Large Boundary Layer Large Reynolds Number: Re = 10 5 Thin Boundary Layer viscous effects are negligible Medium Reynolds Number: Re = 10 Boundary layer: Chemical a thin Engineering region on Department the surface University of a body of Jordan in which Amman viscous 11942, effects Jordan are very important and outside of Tel. which +962 the fluid 5000 behaves essentially as if it were inviscid 12

7 Flow Over Flat Plate : 13 External Flows: Flow Past Objects Symmetric The viscous effects are important several diameters in any direction from the cylinder. The streamlines are essentially symmetric about the center of the cylinder the streamline pattern is the same in front of the cylinder as it is behind the cylinder. 14

8 External Flows: Flow Past Objects Separation As the Reynolds number is increased, the region ahead of the cylinder in which viscous effects are important becomes smaller, The viscous region extending only a short distance ahead of the cylinder. The flow loses its symmetry and the flow separates from the body at the separation location With the increase in Reynolds number, the fluid inertia becomes more important and at some location on the body, denoted the separation location, the fluid s inertia is such that it cannot follow the curved path around to the rear of the body. The result is a separation bubble behind the cylinder in which some of the fluid is actually flowing upstream, against the direction i of the upstream flow 15 External Flows: Flow Past Objects Wake At larger Reynolds numbers, the area affected by the viscous forces is forced farther downstream until it involves only a thin boundary layer on the front portion of the cylinder Irregular, unsteady perhaps turbulent wake region that extends far downstream of the cylinder. The fluid in the region outside of the boundary layer and wake region flows as if it were inviscid. The velocity gradients within the boundary layer and wake regions are much larger than those in the remainder of the flow field The viscous effects are confined to the boundary layer and wake regions. 16

9 Streamlining Streamlining reduces drag by reducing F D,pressure, at the cost of increasing wetted surface area and F D,friction. Goal is to eliminate flow separation and minimize total drag F D Also improves structural acoustics since separation and vortex shedding can excite structural modes. 17 Streamlining 18

10 Streamlining The friction drag is zero for a flat surface normal to flow, and maximum for a flat surface parallel to flow The pressure drag is proportional to the frontal area and to the difference between the pressures acting on the front and back of the immersed body. The pressure drag becomes most significant ifi when the velocity of the fluid is too high h for the fluid to be able to follow the curvature of the body, and thus the fluid separates from the body at some point and creates a very low pressure region in the back. The part of drag that is due directly to wall shear stress τ w is called the skin friction drag (or friction drag F D, friction ) since it is caused by frictional effects, The part that is due directly to pressure P is called the pressure drag (also called the form drag because of its strong dependence on the form or shape of the body) 19 Streamlining The first thought that comes to mind to reduce drag is to streamline a body in order to reduce flow separation and thus to reduce pressure drag Streamlining has opposite effects on pressure and friction drags. It decreases pressure drag by delaying boundary layer separation and thus reducing the pressure difference between the front and back of the body and increases the friction drag by increasing the surface area Optimization study to reduce the drag of a body must consider both effects and must attempt to minimize the sum of the two The minimum total drag 20

11 C D of Common Geometries At higher Reynolds numbers, the drag coefficients for most geometries remain essentially constant This is due to the flow at high Reynolds numbers becoming fully turbulent. 21 C D of Common Geometries 22

12 C D of Common Geometries 23 C D of Common Geometries 24

13 Example As part of the continuing efforts to reduce the drag coefficient and thus to improve the fuel efficiency of cars, the design of side rearview mirrors has changed drastically from a simple circular plate to a streamlined shape. Determine the amount of fuel and money saved per year as a result of replacing a 13-cmdiameter e flat mirror by one with a hemispherical e back. Assume the car is driven 24,000 km a year at an average speed of 95 km/h. The densities of air and gasoline are taken to be 1.20 kg/m 3 and 800 kg/m 3, respectively. The heating value of gasoline is given to be 44,000 kj/kg. Price of gasoline is $0.60/L, and the overall efficiency of the engine to be 30 percent 25 Example Cont. The amount of work done to overcome this drag force and the required energy input for a distance of 26

14 External Flows: Boundary Layers Turbine blades 27 External Flows: Boundary Layers divides the flow over a plate into two regions: The boundary layer region, in which the viscous effects and the velocity changes are significant, viscous shearing forces and The irrotational flow region, in which the frictional effects are negligible and the velocity remains essentially constant. For parallel flow over a flat plate, the pressure drag is zero, and thus the drag coefficient is equal to the friction drag coefficient 28

15 External Flows: Boundary Layers When both sides of a thin plate are subjected to flow, A becomes the total area of the top and bottom surfaces. The Reynolds number at a distance x from the leading edge of a flat plate is 29 External Flows: Boundary Layers Friction Coefficient 30

16 Friction Coefficient the average friction coefficient over the entire plate The local friction coefficients are higher in turbulent flow than they are in laminar flow because of the intense mixing that occurs in the turbulent boundary layer 31 External Flows: Boundary Layers 32

17 Transitional and Turbulent Boundary Layers Turbulent Spots in Transitional Flow No real theories for transitional boundary layers. The turbulent profiles are flatter, have a larger velocity gradient at the wall, and produce a larger boundary layer thickness than do the laminar profiles 33 Transitional and Turbulent Boundary Layers Flat Plate Drag: Analogous to Moody Chart Surface roughness, in general, increases the drag coefficient in turbulent flow. 34

18 Drag on Immersed Objects The critical Reynolds number for flow across a circular cylinder or sphere is about the fluid completely wraps around the cylinder and the two arms of the fluid meet on the rear side of the cylinder in an orderly manner. At higher velocities, The fluid still hugs the cylinder on the frontal side, but it is too fast to remain attached to the surface as it approaches the top (or bottom) of the cylinder. As a result, the boundary layer detaches from the surface, forming a separation region behind the cylinder Flow in the wake region is characterized by periodic vortex formation and pressures much lower than the stagnation point pressure. 35 The high pressure in the vicinity of the stagnation point and the low pressure on the opposite side in the wake produce a net force on the body in the direction of flow. The drag force is primarily due to friction drag at low Reynolds numbers (Re < 10) and to pressure drag at high Reynolds numbers (Re > 5000). 36

19 Drag on Immersed Objects Drag on a Smooth Sphere and Cylinder: 37 Drag on a Smooth Sphere and Cylinder 38

20 Drag on a Smooth Sphere and Cylinder 39 Drag on Immersed Objects If there were not viscous effects acting on an object there would be no friction drag nor any pressure drag. Viscosity causes friction and separation which causes pressure drag. Friction Drag: the part of drag due directly to the shear stress Pressure Drag/Form Drag: the part of drag due directly to the pressure The Drag Coefficient is highly dependent on shape and the Reynolds Number: At the same Reynolds number, the above shapes have the same amount of drag. 40

21 Drag on Immersed Objects For small Reynolds Number flows, the coefficient of drag varies inversely with the Reynolds Number, Re < Effect of Surface Roughness This is done by tripping the boundary layer into turbulence at a lower Reynolds number, Chemical and thus Engineering causing Department the fluid University to close of in Jordan behind Amman the body, 11942, narrowing Jordan the wake Tel. and +962 reducing pressure drag onsiderably. 42

22 Effect of Surface Roughness For blunt bodies such as a circular cylinder or sphere, an increase in the surface roughness may actually decrease the drag coefficient This is done by tripping i the boundary layer into turbulence at a lower Reynolds number, and thus causing the fluid to close in behind the body, narrowing the wake and reducing pressure drag considerably This results in a much smaller drag coefficient and thus drag force for a rough-surfaced cylinder or sphere in a certain range of Reynolds number compared to a smooth one of identical size at the same velocity 43 Drag on Immersed Objects 44

23 Drag on Immersed Objects Shock waves, which cannot exist in subsonic flows, provide a mechanism for the generation of drag that is not present in the relatively low-speed subsonic flows If the velocity of the object is sufficiently large, compressibility effects become important The Mach number and Reynolds number effects are often closely connected because both are directly proportional to the upstream velocity. Independent for Ma < 0.5 Strongly dependent 45 Drag on Immersed Objects blunt and sharp bodies This behavior is due to the nature of the shock wave structure and the accompanying flow separation. The leading edges of wings for subsonic aircraft are usually quite rounded and blunt, while those of supersonic aircraft tend to be quite pointed and sharp 46

24 Drag on Immersed Objects Froude number is a ratio of the free-stream speed to a typical wave speed on the interface of two fluids, such as the surface of the ocean 47 Example Engine oil at 40 C flows over a 5-m-long flat plate with a free-stream velocity of 2 m/s. Determine the drag force acting on the plate per unit width. laminar flow over the entire plate, and the average friction coefficient 48

25 Example A 2.2-cm-outer-diameter pipe is to span across a river at a 30-m-wide section while being completely immersed in water. The average flow velocity of water is 4 m/s and the water temperature is 15 C C. Determine the drag force exerted on the pipe by the river. C D = Example 50

26 Example Cont. 51 Example 52

27 Lift on Immersed Objects The component of the resultant pressure and shear forces that acts normal to the flow direction is called the lift force (or just lift). A typical device designed to produce lift does so by generating a pressure distribution that is different on the top and bottom surfaces V is the upstream velocity of the fluid (or, equivalently, the velocity of a flying body in a quiescent fluid). Lift is generated because the flow velocity at the top surface is higher, and thus the pressure on that surface is lower Because of the asymmetry of the nonsymmetric airfoil,the il pressure distributions on the upper and lower surfaces are different,and a lift is produced even with the angle between the upstream flow and the axis of the object 53 Lift on Immersed Objects Flow starts out with no lift, but the lower fluid stream separates at the trailing edge when the velocity reaches a certain value. This forces the separated upper fluid stream to close in at the trailing edge, initiating clockwise circulation around the airfoil. This clockwise circulation increases the velocity of the upper stream while decreasing that of the lower stream, causing lift A starting vortex of opposite sign (counterclockwise circulation) is then shed downstream and smooth streamlined flow is established over the airfoil 54

28 Lift on Immersed Objects since roughness affects the wall shear, not the pressure, Most common lift-generating devices i.e., airfoils, fans, spoilers on cars, etc. operate in the large Reynolds number range. Viscous effects to lift is usually negligible since the bodies are streamlined, and wall shear is parallel to the surfaces of such devices and thus nearly normal to the direction of lift The most important parameter that affects the lift coefficient is the shape of the object 55 Lift on Immersed Objects Airfoils are specifically designed to generate lift while keeping the drag at a minimum The spoilers s and inverted ed airfoils on racing cars are designed ed for the opposite purpose pose of avoiding lift or even generating negative lift to improve traction and control Most lift generating devices are not symmetrical. Lift can be generated by adjusting the angel of attack of the object. Lift and drag coefficients i of wings are dependent d on angle of attack. At large angles of attack, the boundary layer separates and the wing stalls. The average lift per unit planform area F L /A is called the wing loading, which is simply the ratio of the weight of the aircraft to the planform area of the wings (since lift equals the weight during flying at constant altitude) 56

29 Lift on Immersed Objects The lift acting on an airfoil can be determined by simply integrating the pressure distribution around the airfoil ignoring the very thin boundary layer on the airfoil (zero vorticity, irrotational flow) Net viscous forces are zero for flow past an airfoil il since the pressure changes in the flow direction along the surface, but it remains essentially constant through the boundary layer in a direction normal to the surface In many lift-generating i devices the important quantity is the ratio of the lift to drag developed, To change the lift and drag characteristics of an airfoil is to change the angle of attack. This represents a change in the shape of the object. 57 Lift on Immersed Objects In general, the lift coefficient increases and the drag coefficient decreases with an increase in aspect ratio 58

30 Lift on Immersed Objects Other shape changes can be used to alter the lift and drag when desirable. In modern airplanes it is common to utilize leading edge and trailing edge flaps i.e. change the shape of the airfoil il by the use of movable leading edge and trailing edge flaps 59 Lift on Immersed Objects High-performance airfoils generate lift that is perhaps 100 or more times greater than their drag The minimum flight velocity can be determined from the requirement that the total weight Wof the aircraft be equal to lift and 60

31 Lift Generated by Spinning When the ball is not spinning, the lift is zero because of top bottom symmetry. But when the cylinder is rotated about its axis, the cylinder drags some fluid around because of the no-slip condition and the flow field reflects the superposition of the spinning and nonspinning flows. The stagnation points shift down, and the flow is no longer symmetric about the horizontal plane that passes through the center of the cylinder. The average pressure on the upper half is less than the average pressure at the lower half 61 Lift Generated by Spinning C L strongly depends on rate of rotation. The effect of rate of rotation on C D is small. Baseball, golf, soccer, tennis players utilize spin. Lift generated by rotation is called The Magnus Effect. 62

32 Example 63 Example Cont. 64

33 Example Cont. 65 Example A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m 2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012, determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrus to overcome wing drag. 66

34 Example tennis ball with a mass of lbm and a diameter of 2.52 in is hit at 45 mi/h with a backspin of 4800 rpm. Determine if the ball will fall or rise under the combined effect of gravity and lift due to spinning shortly after being hit in air at 1 atm and 80 F F. The translational and angular velocities of the ball are 67 Example Cont. The ball will drop under the combined effect of gravity and lift due to spinning 68

The effect of back spin on a table tennis ball moving in a viscous fluid.

The 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 information

AE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.

AE 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 information

Basic Fluid Mechanics

Basic 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 information

Chapter 11 EXTERNAL FLOW: DRAG AND LIFT

Chapter 11 EXTERNAL FLOW: DRAG AND LIFT Fluid Mechanics: Fundamentals and Applications, 2nd Edition Yunus A. Cengel, John M. Cimbala McGraw-Hill, 2010 Lecture slides by Mehmet Kanoglu Copyright The McGraw-Hill Companies, Inc. Permission required

More information

Parasite Drag. by David F. Rogers Copyright c 2005 David F. Rogers. All rights reserved.

Parasite 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 information

Lift 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) 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 information

AERODYNAMICS I LECTURE 7 SELECTED TOPICS IN THE LOW-SPEED AERODYNAMICS

AERODYNAMICS 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 information

THE BRIDGE COLLAPSED IN NOVEMBER 1940 AFTER 4 MONTHS OF ITS OPENING TO TRAFFIC!

THE BRIDGE COLLAPSED IN NOVEMBER 1940 AFTER 4 MONTHS OF ITS OPENING TO TRAFFIC! OUTLINE TACOMA NARROWS BRIDGE FLOW REGIME PAST A CYLINDER VORTEX SHEDDING MODES OF VORTEX SHEDDING PARALLEL & OBLIQUE FLOW PAST A SPHERE AND A CUBE SUMMARY TACOMA NARROWS BRIDGE, USA THE BRIDGE COLLAPSED

More information

Welcome to Aerospace Engineering

Welcome 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 information

Reduction of Skin Friction Drag in Wings by Employing Riblets

Reduction 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 information

AF101 to AF109. Subsonic Wind Tunnel Models AERODYNAMICS. A selection of optional models for use with TecQuipment s Subsonic Wind Tunnel (AF100)

AF101 to AF109. Subsonic Wind Tunnel Models AERODYNAMICS. A selection of optional models for use with TecQuipment s Subsonic Wind Tunnel (AF100) Page 1 of 4 A selection of optional models for use with TecQuipment s Subsonic Wind Tunnel (AF100) Dimpled Sphere Drag Model (from AF109) shown inside the TecQuipment AF100 Wind Tunnel. Cylinder, aerofoils,

More information

ROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)

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 information

Wing-Body Combinations

Wing-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 information

Incompressible Flow over Airfoils

Incompressible 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 information

C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory

C-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 information

Subsonic wind tunnel models

Subsonic wind tunnel models aerodynamics AF1300a to AF1300l A selection of optional models for use with TecQuipment s Subsonic Wind Tunnel (AF1300) Dimpled Sphere Drag Model (from AF1300j) shown inside the TecQuipment AF1300 Wind

More information

8d. Aquatic & Aerial Locomotion. Zoology 430: Animal Physiology

8d. Aquatic & Aerial Locomotion. Zoology 430: Animal Physiology 8d. Aquatic & Aerial Locomotion 1 Newton s Laws of Motion First Law of Motion The law of inertia: a body retains its state of rest or motion unless acted on by an external force. Second Law of Motion F

More information

It should be noted that the symmetrical airfoil at zero lift has no pitching moment about the aerodynamic center because the upper and

It 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 information

Exploration Series. AIRPLANE Interactive Physics Simulation Page 01

Exploration 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 information

The subsonic compressibility effect is added by replacing. with

The 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 information

Jet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati

Jet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 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 Lift: is used to support the weight of

More information

Kinematics of Vorticity

Kinematics of Vorticity Kinematics of Vorticity Vorticity Ω Ω= V 2 circumferentially averaged angular velocity of the fluid particles Sum of rotation rates of perpendicular fluid lines Non-zero vorticity doesn t imply spin.ω=0.

More information

ME 239: Rocket Propulsion. Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD

ME 239: Rocket Propulsion. Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD ME 239: Rocket Propulsion Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD 1 Commonly acting forces on a vehicle flying in a planetary atmosphere: Thrust Aerodynamic

More information

EXPERIMENTAL 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 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 information

Lecture # 08: Boundary Layer Flows and Drag

Lecture # 08: Boundary Layer Flows and Drag AerE 311L & AerE343L Lecture Notes Lecture # 8: Boundary Layer Flows and Drag Dr. Hui H Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A y AerE343L #4: Hot wire measurements

More information

Why does a golf ball have dimples?

Why does a golf ball have dimples? Página 1 de 5 Why does a golf ball have dimples? page 1 A golf ball can be driven great distances down the fairway. How is this possible? Is the drive only dependent on the strength of the golfer or are

More information

Flight Corridor. The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor.

Flight Corridor. The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor. Flight Corridor The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor. The subsonic Boeing 747 and supersonic Concorde have flight corridors

More information

DEFINITIONS. Aerofoil

DEFINITIONS. 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 information

AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK

AERODYNAMIC 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 information

THE CURVE OF THE CRICKET BALL SWING AND REVERSE SWING

THE CURVE OF THE CRICKET BALL SWING AND REVERSE SWING Parabola Volume 32, Issue 2 (1996) THE CURVE OF THE CRICKET BALL SWING AND REVERSE SWING Frank Reid 1 It is a well known fact in cricket that the new ball when bowled by a fast bowler will often swing

More information

POWERED FLIGHT HOVERING FLIGHT

POWERED 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 information

Aerodynamic Analysis of a Symmetric Aerofoil

Aerodynamic 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 information

Aerodynamic Terms. Angle of attack is the angle between the relative wind and the wing chord line. [Figure 2-2] Leading edge. Upper camber.

Aerodynamic 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 information

Detailed study 3.4 Topic Test Investigations: Flight

Detailed 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 information

Effect of Co-Flow Jet over an Airfoil: Numerical Approach

Effect 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 information

Drag Divergence and Wave Shock. A Path to Supersonic Flight Barriers

Drag 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 information

J. 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. 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 information

Experimental Investigation Of Flow Past A Rough Surfaced Cylinder

Experimental Investigation Of Flow Past A Rough Surfaced Cylinder (AET- 29th March 214) RESEARCH ARTICLE OPEN ACCESS Experimental Investigation Of Flow Past A Rough Surfaced Cylinder Monalisa Mallick 1, A. Kumar 2 1 (Department of Civil Engineering, National Institute

More information

Write important assumptions used in derivation of Bernoulli s equation. Apart from an airplane wing, give an example based on Bernoulli s principle

Write important assumptions used in derivation of Bernoulli s equation. Apart from an airplane wing, give an example based on Bernoulli s principle HW#3 Sum07 #1. Answer in 4 to 5 lines in the space provided for each question: (a) A tank partially filled with water has a balloon well below the free surface and anchored to the bottom by a string. The

More information

THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL. By Mehrdad Ghods

THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL. By Mehrdad Ghods THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL By Mehrdad Ghods Technical Communication for Engineers The University of British Columbia July 23, 2001 ABSTRACT Theory of Wings and Wind

More information

A COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE

A COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE 28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES A COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE Jung-Hyun Kim*, Kyu-Hong

More information

ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT

ANALYSIS 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 information

External Tank- Drag Reduction Methods and Flow Analysis

External 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 information

Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur

Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur Lecture - 12 Design Considerations: Aerofoil Selection Good morning friends. The last lecture

More information

Agood tennis player knows instinctively how hard to hit a ball and at what angle to get the ball over the. Ball Trajectories

Agood tennis player knows instinctively how hard to hit a ball and at what angle to get the ball over the. Ball Trajectories 42 Ball Trajectories Factors Influencing the Flight of the Ball Nathalie Tauziat, France By Rod Cross Introduction Agood tennis player knows instinctively how hard to hit a ball and at what angle to get

More information

Applications of Bernoulli s principle. Principle states that areas with faster moving fluids will experience less pressure

Applications of Bernoulli s principle. Principle states that areas with faster moving fluids will experience less pressure Applications of Bernoulli s principle Principle states that areas with faster moving fluids will experience less pressure Artery o When blood flows through narrower regions of arteries, the speed increases

More information

Computational Analysis of Cavity Effect over Aircraft Wing

Computational 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 information

Avai 193 Fall 2016 Laboratory Greensheet

Avai 193 Fall 2016 Laboratory Greensheet Avai 193 Fall 2016 Laboratory Greensheet Lab Report 1 Title: Instrumentation Test Technique Research Process: Break into groups of 4 people. These groups will be the same for all of the experiments performed

More information

Bioreactor System ERT 314. Sidang /2011

Bioreactor System ERT 314. Sidang /2011 Bioreactor System ERT 314 Sidang 1 2010/2011 Chapter 2:Types of Bioreactors Week 4 Flow Patterns in Agitated Tanks The flow pattern in an agitated tank depends on the impeller design, the properties of

More information

CHAPTER-1 INTRODUCTION

CHAPTER-1 INTRODUCTION CHAPTER-1 INTRODUCTION 1 1.1 Introduction This investigation documents the aerodynamic characteristics of four profiles, as cylinder, sphere, symmetrical aerofoil (NACA 0015) and cambered aerofoil (NACA

More information

Aerodynamic Performance Enhancement of a NACA Airfoil Using Supersonic Channel Airfoil Design

Aerodynamic Performance Enhancement of a NACA Airfoil Using Supersonic Channel Airfoil Design 46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-300 7-10 January 2008, Reno, Nevada Aerodynamic Performance Enhancement of a NACA 66-206 Airfoil Using Supersonic Channel Airfoil Design David

More information

Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft

Aerodynamic 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 information

Aerodynamics Principles

Aerodynamics 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 information

Lecture # 08: Boundary Layer Flows and Controls

Lecture # 08: Boundary Layer Flows and Controls AerE 344 Lecture Notes Lecture # 8: Boundary Layer Flows and Controls Dr. Hui Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A Flow Separation on an Airfoil Quantification

More information

Uncontrolled copy not subject to amendment. Principles of Flight

Uncontrolled 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 information

Numerical Simulations of a Train of Air Bubbles Rising Through Stagnant Water

Numerical Simulations of a Train of Air Bubbles Rising Through Stagnant Water Numerical Simulations of a Train of Air Bubbles Rising Through Stagnant Water Hong Xu, Chokri Guetari ANSYS INC. Abstract Transient numerical simulations of the rise of a train of gas bubbles in a liquid

More information

Aero Club. Introduction to Flight

Aero 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 information

Principles of glider flight

Principles 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 information

Incompressible Potential Flow. Panel Methods (3)

Incompressible 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 information

Engineering Flettner Rotors to Increase Propulsion

Engineering Flettner Rotors to Increase Propulsion Engineering Flettner Rotors to Increase Propulsion Author: Chance D. Messer Mentor: Jeffery R. Wehr Date: April 11, 2016 Advanced STEM Research Laboratory, Odessa High School, 107 E 4 th Avenue, Odessa

More information

PRE-TEST Module 2 The Principles of Flight Units /60 points

PRE-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 information

AN EXPERIMENTAL STUDY OF THE EFFECTS OF SWEPT ANGLE ON THE BOUNDARY LAYER OF THE 2D WING

AN EXPERIMENTAL STUDY OF THE EFFECTS OF SWEPT ANGLE ON THE BOUNDARY LAYER OF THE 2D WING AN EXPERIMENTAL STUDY OF THE EFFECTS OF SWEPT ANGLE ON THE BOUNDARY LAYER OF THE 2D WING A. Davari *, M.R. Soltani, A.Tabrizian, M.Masdari * Assistant Professor, Department of mechanics and Aerospace Engineering,

More information

Irrigation &Hydraulics Department lb / ft to kg/lit.

Irrigation &Hydraulics Department lb / ft to kg/lit. CAIRO UNIVERSITY FLUID MECHANICS Faculty of Engineering nd Year CIVIL ENG. Irrigation &Hydraulics Department 010-011 1. FLUID PROPERTIES 1. Identify the dimensions and units for the following engineering

More information

Aerodynamic characteristics around the stalling angle of the discus using a PIV

Aerodynamic characteristics around the stalling angle of the discus using a PIV 10TH INTERNATIONAL SYMPOSIUM ON PARTICLE IMAGE VELOCIMETRY PIV13 Delft, The Netherlands, July 1-3, 2013 Aerodynamic characteristics around the stalling angle of the discus using a PIV Kazuya Seo 1 1 Department

More information

HEFAT th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics July 2012 Malta

HEFAT th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics July 2012 Malta HEFAT212 9 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 16 18 July 212 Malta AN EXPERIMENTAL STUDY OF SWEEP ANGLE EFFECTS ON THE TRANSITION POINT ON A 2D WING BY USING

More information

Low Speed Wind Tunnel Wing Performance

Low 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 information

The water supply for a hydroelectric plant is a reservoir with a large surface area. An outlet pipe takes the water to a turbine.

The water supply for a hydroelectric plant is a reservoir with a large surface area. An outlet pipe takes the water to a turbine. Fluids 1a. [1 mark] The water supply for a hydroelectric plant is a reservoir with a large surface area. An outlet pipe takes the water to a turbine. State the difference in terms of the velocity of the

More information

Aerodynamic behavior of a discus

Aerodynamic behavior of a discus Available online at www.sciencedirect.com Procedia Engineering 34 (2012 ) 92 97 9 th Conference of the International Sports Engineering Association (ISEA) Aerodynamic behavior of a discus Kazuya Seo a*,

More information

EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT

EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT Chapter-6 EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT 6.1 Introduction The gurney flap (wicker bill) was a small flat tab projecting from the trailing edge of a wing. Typically it

More information

CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS

CFD 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 information

CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS

CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS Colloquium FLUID DYNAMICS 2008 Institute of Thermomechanics AS CR, v.v.i., Prague, October 22-24, 2008 p.1 CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS Vladimír Horák 1, Dalibor

More information

Influence of rounding corners on unsteady flow and heat transfer around a square cylinder

Influence of rounding corners on unsteady flow and heat transfer around a square cylinder Influence of rounding corners on unsteady flow and heat transfer around a square cylinder S. K. Singh Deptt. of Mech. Engg., M. B. M. Engg. College / J. N. V. University, Jodhpur, Rajasthan, India Abstract

More information

No Description Direction Source 1. Thrust

No 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 information

CFD Analysis ofwind Turbine Airfoil at Various Angles of Attack

CFD Analysis ofwind Turbine Airfoil at Various Angles of Attack IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 13, Issue 4 Ver. II (Jul. - Aug. 2016), PP 18-24 www.iosrjournals.org CFD Analysis ofwind Turbine

More information

Reynolds Number Effects on Leading Edge Vortices

Reynolds 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 information

Theory of Flight Stalls. References: FTGU pages 18, 35-38

Theory 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 information

AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING

AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING ICAS 2002 CONGRESS AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING Yoshiaki NAKAMURA (nakamura@nuae.nagoya-u.ac.jp) Takafumi YAMADA (yamada@nuae.nagoya-u.ac.jp) Department of Aerospace Engineering,

More information

SEMI-SPAN TESTING IN WIND TUNNELS

SEMI-SPAN TESTING IN WIND TUNNELS 25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES SEMI-SPAN TESTING IN WIND TUNNELS S. Eder, K. Hufnagel, C. Tropea Chair of Fluid Mechanics and Aerodynamics, Darmstadt University of Technology

More information

Tidal streams and tidal stream energy device design

Tidal streams and tidal stream energy device design Tidal streams and tidal stream energy device design This technical article introduces fundamental characteristics of tidal streams and links these to the power production of tidal stream energy devices.

More information

EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES

EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES Abdul Ahad Khan 1, Abhishek M. B 2, Tresa Harsha P George 3 1 Under Graduate student, Department of Aeronautical

More information

A Numerical Simulation Comparing the Efficiencies of Tubercle Versus Straight Leading Edge Airfoils for a Darrieus Vertical Axis Wind Turbine

A Numerical Simulation Comparing the Efficiencies of Tubercle Versus Straight Leading Edge Airfoils for a Darrieus Vertical Axis Wind Turbine A Numerical Simulation Comparing the Efficiencies of Tubercle Versus Straight Leading Edge Airfoils for a Darrieus Vertical Axis Wind Turbine By: Ross Neal Abstract: The efficiencies of sinusoidal and

More information

SUBPART C - STRUCTURE

SUBPART C - STRUCTURE SUBPART C - STRUCTURE GENERAL CS 23.301 Loads (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by

More information

. In an elevator accelerating upward (A) both the elevator accelerating upward (B) the first is equations are valid

. In an elevator accelerating upward (A) both the elevator accelerating upward (B) the first is equations are valid IIT JEE Achiever 2014 Ist Year Physics-2: Worksheet-1 Date: 2014-06-26 Hydrostatics 1. A liquid can easily change its shape but a solid cannot because (A) the density of a liquid is smaller than that of

More information

DEPARTMENT OF THE NAVY NAVAL UNDERSEA WARFARE CENTER DIVISION NEWPORT

DEPARTMENT OF THE NAVY NAVAL UNDERSEA WARFARE CENTER DIVISION NEWPORT DEPARTMENT OF THE NAVY NAVAL UNDERSEA WARFARE CENTER DIVISION NEWPORT gsop P OFFICE OF COUNSEL (PATENTS) 14 1176 HOWELL STREET Q w BUILDING 112T, CODE OOOC NEWPORT, RHODE ISLAND 02841-1708 PHONE: 401 832-4736

More information

Experimental and Theoretical Investigation for the Improvement of the Aerodynamic Characteristic of NACA 0012 airfoil

Experimental and Theoretical Investigation for the Improvement of the Aerodynamic Characteristic of NACA 0012 airfoil International Journal of Mining, Metallurgy & Mechanical Engineering (IJMMME) Volume 2, Issue 1 (214) ISSN 232 46 (Online) Experimental and Theoretical Investigation for the Improvement of the Aerodynamic

More information

CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT

CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT Magnus effect, simulation, air flow Patryk SOKOŁOWSKI *, Jacek CZARNIGOWSKI **, Paweł MAGRYTA *** CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT Abstract The article presents

More information

2 Available: 1390/08/02 Date of returning: 1390/08/17 1. A suction cup is used to support a plate of weight as shown in below Figure. For the conditio

2 Available: 1390/08/02 Date of returning: 1390/08/17 1. A suction cup is used to support a plate of weight as shown in below Figure. For the conditio 1. A suction cup is used to support a plate of weight as shown in below Figure. For the conditions shown, determine. 2. A tanker truck carries water, and the cross section of the truck s tank is shown

More information

Aerofoil Design for Man Powered Aircraft

Aerofoil Design for Man Powered Aircraft Man Powered Aircraft Group Aerofoil Design for Man Powered Aircraft By F. X. Wortmann Universitat Stuttgart From the Second Man Powered Aircraft Group Symposium Man Powered Flight The Way Ahead 7 th February

More information

Figure 1 Figure 1 shows the involved forces that must be taken into consideration for rudder design. Among the most widely known profiles, the most su

Figure 1 Figure 1 shows the involved forces that must be taken into consideration for rudder design. Among the most widely known profiles, the most su THE RUDDER starting from the requirements supplied by the customer, the designer must obtain the rudder's characteristics that satisfy such requirements. Subsequently, from such characteristics he must

More information

Static Fluids. **All simulations and videos required for this package can be found on my website, here:

Static Fluids. **All simulations and videos required for this package can be found on my website, here: DP Physics HL Static Fluids **All simulations and videos required for this package can be found on my website, here: http://ismackinsey.weebly.com/fluids-hl.html Fluids are substances that can flow, so

More information

STUDY OF VARIOUS NACA SERIES AEROFOIL SECTIONS AND WING CONTOUR GENERATION USING CATIA V5

STUDY OF VARIOUS NACA SERIES AEROFOIL SECTIONS AND WING CONTOUR GENERATION USING CATIA V5 STUDY OF VARIOUS NACA SERIES AEROFOIL SECTIONS AND WING CONTOUR GENERATION USING CATIA V5 Pawan Kumar Department of Aeronautical Engineering, Desh Bhagat University, Punjab, India ABSTRACT Aerofoil is

More information

Tim Lee s journal publications

Tim Lee s journal publications Tim Lee s journal publications 82. Lee, T., and Tremblay-Dionne, V., (2018) Impact of wavelength and amplitude of a wavy ground on a static NACA 0012 airfoil submitted to Journal of Aircraft (paper in

More information

CFD Analysis of Effect of Variation in Angle of Attack over NACA 2412 Airfoil through the Shear Stress Transport Turbulence Model

CFD 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 information

The Fly Higher Tutorial IV

The 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 information

FLUID MECHANICS Time: 1 hour (ECE-301) Max. Marks :30

FLUID MECHANICS Time: 1 hour (ECE-301) Max. Marks :30 B.Tech. [SEM III(ME&CE)] QUIZ TEST-1 (Session : 2013-14) Time: 1 hour (ECE-301) Max. Marks :30 Note: Attempt all questions. PART A Q1. The velocity of the fluid filling a hollow cylinder of radius 0.1

More information

Study on the Shock Formation over Transonic Aerofoil

Study on the Shock Formation over Transonic Aerofoil Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 113-118 Research India Publications http://www.ripublication.com/aasa.htm Study on the Shock Formation over

More information

CFD Study of Solid Wind Tunnel Wall Effects on Wing Characteristics

CFD Study of Solid Wind Tunnel Wall Effects on Wing Characteristics Indian Journal of Science and Technology, Vol 9(45), DOI :10.17485/ijst/2016/v9i45/104585, December 2016 ISSN (Print) : 0974-6846 ISSN (Online) : 0974-5645 CFD Study of Solid Wind Tunnel Wall Effects on

More information

Principles of Flight. Chapter 4. From the Library at Introduction. Structure of the Atmosphere

Principles 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 information

BUILD AND TEST A WIND TUNNEL

BUILD 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 information

PRINCIPLES OF FLIGHT

PRINCIPLES OF FLIGHT CHAPTER 3 PRINCIPLES OF FLIGHT INTRODUCTION Man has always wanted to fly. Legends from the very earliest times bear witness to this wish. Perhaps the most famous of these legends is the Greek myth about

More information