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

Size: px
Start display at page:

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

Transcription

1 Question Given a stream function for a cylinder in a uniform flow with circulation: R Γ r ψ = U r sinθ + ln r π R a) Sketch the flow pattern in terms of streamlines. b) Derive an expression for the angular position, θ, of the front and rear stagnation points in terms of the circulation, Γ, and the freestream velocity U. c) The circulation around a spinning cylinder causes the stagnation points to be displaced by 30 o downwards. i) Calculate the magnitudes of the flow velocity at the top and bottom of the cylinder, and the corresponding surface pressure coefficients. ii) Using the Kutta-Joukowski Theorem, evaluate the lift coefficient per unit span. Page of 7

2 Question A thin aerofoil has a circular arc camber line with a maximum camber of.5%. The camber line can be approximated by: y c ax x = c c where a is a constant. Given that the general loading on an aerofoil is given by: k + cosθ = 0 sin sinθ n= ( θ ) U A + A n nθ where: A 0 = α π π 0 dy dθ dx and: A n = π π 0 dy cos nθdθ dx a) Determine the parameters A 0 and A n (n= to infinity) [9 marks] b) Derive the equation for the lift coefficient C L in terms of A 0 and A. [9 marks] c) Calculate the magnitude of constant a, and the zero lift angle of attack, and then sketch the lift curve. [7 marks] Hint: Remember the transformation between Cartesian and polar coordinates. Page of 7

3 Question 3 A wing of span, b, and a planform area, S, with an elliptic lift distribution, can be described by the equation below: y Γ ( y) = Γ0 s where y is the spanwise ordinate and s is the span (maximum y). The wing is to be modelled by a horseshoe vortex of strength, Γ 0, and span, b 0. i) Show that for the horseshow vortex model: πb b 0 = 4 and b C 0 0 L = Γ V S ii) Use the Biot-Savart Law for a straight vortex segment filament, given below, to show that the vertical velocity, w, induced on the plane of symmetry of the horseshoe vortex is: Γ w( x) = 0 + πb0 x + ( b ) 0 x where x is the longitudinal distance from the wing quarter chord (positive downstream). iii) Sketch the variation of w with x. Page 3 of 7

4 Question 4 For a laminar boundary layer on a flat plate at zero angle of incidence, the velocity profile is assumed to have a profile: u U y y = δ δ a) Obtain the relationships for displacement thickness, δ *, and momentum thickness, θ, in terms of the boundary layer thickness, δ. b) Determine the expression for: i) how the boundary layer thickness, δ, varies with the distance from the plate leading edge, x. ii) the variation of momentum thickness, θ, with distance from the plate leading edge, x. Note that: dθ C f = dx Page 4 of 7

5 Question 5 a) Describe the physical characteristics of a turbulent boundary layer, including a description of each physical layer, and a plot of the variation between u + and y + within a turbulent boundary layer. [9 marks] b) For a turbulent boundary layer on a flat plate at zero angle of attack, the boundary layer velocity profile can be modelled as: u y 7 = U δ Given that the local skin friction coefficient, C f, is: C f = Re 4 x where Reynolds number based on distance, x, from the fictitious origin of the turbulent boundary layer thickness, determine an expression for the variation of boundary layer thickness, δ, with x. [6 marks] Page 5 of 7

6 Question 6 The diamond-wedge high speed aerofoil shown in Figure Q6 below is to be tested at an angle of attack of α=5 o to a Mach 3.0 free stream air flow. a) Sketch the flow structure around the aerofoil showing all shock waves and expansion fans. [6 marks] b) Using the tables/charts provided, use Shock-Expansion theory to calculate the pressure ratios; p /p, p 3 /p etc. for each surface. [ marks] c) Calculate the theoretical lift and drag coefficients per unit span. [7 marks] α 0 o M Figure Q6 Page 6 of 7

7 Question 7 a) An aircraft is flying at a velocity of 40m/s at low altitude, where standard sea level conditions can be assumed (.03bar, 88K). Calculate: i) The Mach number the aircraft is flying at, ii) The pressure measured by a nose mounted pitot tube, iii) The static pressure measured at a point on the upper wing surface where the local velocity is sonic (M=.0) iv) The local velocity at this point. [ marks] b) A model of the same aircraft is tested in a wind tunnel which works by inducing atmospheric air through a smooth contraction into the working section and then into a low pressure system. If the freestream Mach number in the tunnel working section is to match the real flight value, calculate: i) The corresponding static pressure and freestream velocity in the working section. ii) The pressure measured by the nose mounted pitot tube. c) Given the difference in freestream velocity and model scale between flight and wind tunnel test, comment on the likely accuracy of the wind tunnel measurements. [3 marks] Page 7 of 7

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

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

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

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

### INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad

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

### 1. Fluid Dynamics Around Airfoils

1. Fluid Dynamics Around Airfoils Two-dimensional flow around a streamlined shape Foces on an airfoil Distribution of pressue coefficient over an airfoil The variation of the lift coefficient with the

### Steady waves in compressible flow

Chapter Steady waves in compressible flow. Oblique shock waves Figure. shows an oblique shock wave produced when a supersonic flow is deflected by an angle. Figure.: Flow geometry near a plane oblique

### Syllabus for AE3610, Aerodynamics I

Syllabus for AE3610, Aerodynamics I Current Catalog Data: AE 3610 Aerodynamics I Credit: 4 hours A study of incompressible aerodynamics of flight vehicles with emphasis on combined application of theory

### Fundamentals of Aerodynamics

Fundamentals of Aerodynamics Fourth Edition John D. Anderson, Jr. Curator of Aerodynamics National Air and Space Museum Smithsonian Institution and Professor Emeritus University of Maryland Me Graw Hill

### FUNDAMENTALS OF AERODYNAMICS

*A \ FUNDAMENTALS OF AERODYNAMICS Second Edition John D. Anderson, Jr. Professor of Aerospace Engineering University of Maryland H ' McGraw-Hill, Inc. New York St. Louis San Francisco Auckland Bogota Caracas

### a) Derive general expressions for the stream function Ψ and the velocity potential function φ for the combined flow. [12 Marks]

Question 1 A horizontal irrotational flow system results from the combination of a free vortex, rotating anticlockwise, of strength K=πv θ r, located with its centre at the origin, with a uniform flow

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

Question 1 (a) onsider a wing of finite span with an elliptic circulation distribution: Γ( y) Γo y + b = 1, - s y s where s=b/ denotes the wing semi-span. Use this equation, in conjunction with the Kutta-Joukowsky

### University of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005

University of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005 Answer both questions. Question 1 is worth 30 marks and question

### PART 1B EXPERIMENTAL ENGINEERING. SUBJECT: FLUID MECHANICS & HEAT TRANSFER LOCATION: HYDRAULICS LAB (Gnd Floor Inglis Bldg) BOUNDARY LAYERS AND DRAG

1 PART 1B EXPERIMENTAL ENGINEERING SUBJECT: FLUID MECHANICS & HEAT TRANSFER LOCATION: HYDRAULICS LAB (Gnd Floor Inglis Bldg) EXPERIMENT T3 (LONG) BOUNDARY LAYERS AND DRAG OBJECTIVES a) To measure the velocity

### Fundamentals of Aerodynamits

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

### Inviscid & Incompressible flow

< 3.1. Introduction and Road Map > Basic aspects of inviscid, incompressible flow Bernoulli s Equation Laplaces s Equation Some Elementary flows Some simple applications 1.Venturi 2. Low-speed wind tunnel

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

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

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

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

### Flight Vehicle Terminology

Flight Vehicle Terminology 1.0 Axes Systems There are 3 axes systems which can be used in Aeronautics, Aerodynamics & Flight Mechanics: Ground Axes G(x 0, y 0, z 0 ) Body Axes G(x, y, z) Aerodynamic Axes

### Fluid Mechanics Prof. T. I. Eldho Department of Civil Engineering Indian Institute of Technology, Bombay

Fluid Mechanics Prof. T. I. Eldho Department of Civil Engineering Indian Institute of Technology, Bombay Lecture No. # 35 Boundary Layer Theory and Applications Welcome back to the video course on fluid

### Introduction to Aerospace Engineering

4. Basic Fluid (Aero) Dynamics Introduction to Aerospace Engineering Here, we will try and look at a few basic ideas from the complicated field of fluid dynamics. The general area includes studies of incompressible,

### Module3: Waves in Supersonic Flow Lecture14: Waves in Supersonic Flow (Contd.)

1 Module3: Waves in Supersonic Flow Lecture14: Waves in Supersonic Flow (Contd.) Mach Reflection: The appearance of subsonic regions in the flow complicates the problem. The complications are also encountered

### 6.1 According to Handbook of Chemistry and Physics the composition of air is

6. Compressible flow 6.1 According to Handbook of Chemistry and Physics the composition of air is From this, compute the gas constant R for air. 6. The figure shows a, Pitot-static tube used for velocity

### Masters in Mechanical Engineering Aerodynamics 1 st Semester 2015/16

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

### Iran University of Science & Technology School of Mechanical Engineering Advance Fluid Mechanics

1. Consider a sphere of radius R immersed in a uniform stream U0, as shown in 3 R Fig.1. The fluid velocity along streamline AB is given by V ui U i x 1. 0 3 Find (a) the position of maximum fluid acceleration

### Incompressible Flow Over Airfoils

Chapter 7 Incompressible Flow Over Airfoils Aerodynamics of wings: -D sectional characteristics of the airfoil; Finite wing characteristics (How to relate -D characteristics to 3-D characteristics) How

### Applied Fluid Mechanics

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

### Random Problems. Problem 1 (30 pts)

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

### Department of Energy Sciences, LTH

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

### High Speed Aerodynamics. Copyright 2009 Narayanan Komerath

Welcome to High Speed Aerodynamics 1 Lift, drag and pitching moment? Linearized Potential Flow Transformations Compressible Boundary Layer WHAT IS HIGH SPEED AERODYNAMICS? Airfoil section? Thin airfoil

### PEMP ACD2505. M.S. Ramaiah School of Advanced Studies, Bengaluru

Two-Dimensional Potential Flow Session delivered by: Prof. M. D. Deshpande 1 Session Objectives -- At the end of this session the delegate would have understood PEMP The potential theory and its application

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

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

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

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

### Lifting Airfoils in Incompressible Irrotational Flow. AA210b Lecture 3 January 13, AA210b - Fundamentals of Compressible Flow II 1

Lifting Airfoils in Incompressible Irrotational Flow AA21b Lecture 3 January 13, 28 AA21b - Fundamentals of Compressible Flow II 1 Governing Equations For an incompressible fluid, the continuity equation

### Department of Mechanical Engineering

Department of Mechanical Engineering AMEE401 / AUTO400 Aerodynamics Instructor: Marios M. Fyrillas Email: eng.fm@fit.ac.cy HOMEWORK ASSIGNMENT #2 QUESTION 1 Clearly there are two mechanisms responsible

### An Internet Book on Fluid Dynamics. Joukowski Airfoils

An Internet Book on Fluid Dynamics Joukowski Airfoils One of the more important potential flow results obtained using conformal mapping are the solutions of the potential flows past a family of airfoil

### AE 311 Incompressible Flow Fall 2016 Homework Set # 7 Due: In class on Wednesday 2 November

AE 311 Incompressible Flow Fall 2016 Homework Set # 7 Due: In class on Wednesday 2 November Show all your equations, data, and work to receive full credit. Clearly indicate your answers. 1. (20%) Assume

Low Speed Aerodynamics Notes 5: Potential ti Flow Method Objective: Get a method to describe flow velocity fields and relate them to surface shapes consistently. Strategy: Describe the flow field as the

### All that begins... peace be upon you

All that begins... peace be upon you Faculty of Mechanical Engineering Department of Thermo Fluids SKMM 2323 Mechanics of Fluids 2 «An excerpt (mostly) from White (2011)» ibn Abdullah May 2017 Outline

### Bluff Body, Viscous Flow Characteristics ( Immersed Bodies)

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

### Airfoils and Wings. Eugene M. Cliff

Airfoils and Wings Eugene M. Cliff 1 Introduction The primary purpose of these notes is to supplement the text material related to aerodynamic forces. We are mainly interested in the forces on wings and

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

Definitions Chapter 3 Standard atmosphere: A model of the atmosphere based on the aerostatic equation, the perfect gas law, an assumed temperature distribution, and standard sea level conditions. Temperature:

### Lecture-4. Flow Past Immersed Bodies

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

LINE INTEGRALS LINE INTEGRALS IN 2 DIMENSIONAL CARTESIAN COORDINATES Question 1 Evaluate the integral ( x + 2y) dx, C where C is the path along the curve with equation y 2 = x + 1, from ( ) 0,1 to ( )

### Experimental Aerodynamics. Experimental Aerodynamics

Lecture 3: Vortex shedding and buffeting G. Dimitriadis Buffeting! All structures exposed to a wind have the tendency to vibrate.! These vibrations are normally of small amplitude and have stochastic character!

### Stability and Control

Stability and Control Introduction An important concept that must be considered when designing an aircraft, missile, or other type of vehicle, is that of stability and control. The study of stability is

### Tutorial 10. Boundary layer theory

Tutorial 10 Boundary layer theory 1. If the velocity distribution law in a laminar boundary layer over a flat plate is assumes to be of the form, determine the velocity distribution law. At y = 0, u= 0

### Lab Reports Due on Monday, 11/24/2014

AE 3610 Aerodynamics I Wind Tunnel Laboratory: Lab 4 - Pressure distribution on the surface of a rotating circular cylinder Lab Reports Due on Monday, 11/24/2014 Objective In this lab, students will be

### Analyses of Diamond - Shaped and Circular Arc Airfoils in Supersonic Wind Tunnel Airflows

Analyses of Diamond - Shaped and Circular Arc Airfoils in Supersonic Wind Tunnel Airflows Modo U. P, Chukwuneke J. L, Omenyi Sam 1 Department of Mechanical Engineering, Nnamdi Azikiwe University, Awka,

### OUTLINE FOR Chapter 3

013/4/ OUTLINE FOR Chapter 3 AERODYNAMICS (W-1-1 BERNOULLI S EQUATION & integration BERNOULLI S EQUATION AERODYNAMICS (W-1-1 013/4/ BERNOULLI S EQUATION FOR AN IRROTATION FLOW AERODYNAMICS (W-1-.1 VENTURI

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

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

### Separation in three-dimensional steady flow. Part 3: TOPOLOGY OF SOME REMARKABLE THREE-DIMENSIONAL FLOWS

Separation in three-dimensional steady flow Part 3: TOPOLOGY OF SOME REMARKABLE THREE-DIMENSIONAL FLOWS H. Werlé. Onera Separation on a blunt body Separation on a blunt body Two-vortex structure. Skin

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

### Relaminerization of a Highly Accelerated Flow on a Convex Curvature

Relaminerization of a Highly Accelerated Flow on a Convex Curvature Abstract Relaminarization of turbulent flow is a process by which the mean flow reverts to an effectively laminar state. The phenomenon

### List of symbols. Latin symbols. Symbol Property Unit

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

### Aerodynamic Rotor Model for Unsteady Flow and Wake Impact

Aerodynamic Rotor Model for Unsteady Flow and Wake Impact N. Bampalas, J. M. R. Graham Department of Aeronautics, Imperial College London, Prince Consort Road, London, SW7 2AZ June 28 1 (Steady Kutta condition)

### S.E. (Mech.) (First Sem.) EXAMINATION, (Common to Mech/Sandwich) FLUID MECHANICS (2008 PATTERN) Time : Three Hours Maximum Marks : 100

Total No. of Questions 12] [Total No. of Printed Pages 8 Seat No. [4262]-113 S.E. (Mech.) (First Sem.) EXAMINATION, 2012 (Common to Mech/Sandwich) FLUID MECHANICS (2008 PATTERN) Time : Three Hours Maximum

### 1. Introduction, tensors, kinematics

1. Introduction, tensors, kinematics Content: Introduction to fluids, Cartesian tensors, vector algebra using tensor notation, operators in tensor form, Eulerian and Lagrangian description of scalar and

### Some Basic Plane Potential Flows

Some Basic Plane Potential Flows Uniform Stream in the x Direction A uniform stream V = iu, as in the Fig. (Solid lines are streamlines and dashed lines are potential lines), possesses both a stream function

### PPT ON LOW SPEED AERODYNAMICS B TECH IV SEMESTER (R16) AERONAUTICAL ENGINEERING. Prepared by Dr. A. Barai. Mr. N. Venkata Raghavendra

PPT ON LOW SPEED AERODYNAMICS B TECH IV SEMESTER (R16) AERONAUTICAL ENGINEERING Prepared by Dr. A. Barai Professor Mr. N. Venkata Raghavendra Associate Professor INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous)

### 1. Introduction - Tutorials

1. Introduction - Tutorials 1.1 Physical properties of fluids Give the following fluid and physical properties(at 20 Celsius and standard pressure) with a 4-digit accuracy. Air density : Water density

### Contents. I Introduction 1. Preface. xiii

Contents Preface xiii I Introduction 1 1 Continuous matter 3 1.1 Molecules................................ 4 1.2 The continuum approximation.................... 6 1.3 Newtonian mechanics.........................

### UNIT 4 FORCES ON IMMERSED BODIES. Lecture-01

1 UNIT 4 FORCES ON IMMERSED BODIES Lecture-01 Forces on immersed bodies When a body is immersed in a real fluid, which is flowing at a uniform velocity U, the fluid will exert a force on the body. The

### Experimental Aerodynamics. Experimental Aerodynamics

Lecture 6: Slender Body Aerodynamics G. Dimitriadis Slender bodies! Wings are only one of the types of body that can be tested in a wind tunnel.! Although wings play a crucial role in aeronautical applications

### Wings and Bodies in Compressible Flows

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

### FLUID MECHANICS. Chapter 9 Flow over Immersed Bodies

FLUID MECHANICS Chapter 9 Flow over Immersed Bodies CHAP 9. FLOW OVER IMMERSED BODIES CONTENTS 9.1 General External Flow Characteristics 9.3 Drag 9.4 Lift 9.1 General External Flow Characteristics 9.1.1

### Numerical Investigation of Wind Tunnel Wall Effects on a Supersonic Finned Missile

16 th International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 May 26-28, 2015, E-Mail: asat@mtc.edu.eg Military Technical College, Kobry Elkobbah, Cairo, Egypt Tel : +(202) 24025292

### Laminar Flow. Chapter ZERO PRESSURE GRADIENT

Chapter 2 Laminar Flow 2.1 ZERO PRESSRE GRADIENT Problem 2.1.1 Consider a uniform flow of velocity over a flat plate of length L of a fluid of kinematic viscosity ν. Assume that the fluid is incompressible

### Water is sloshing back and forth between two infinite vertical walls separated by a distance L: h(x,t) Water L

ME9a. SOLUTIONS. Nov., 29. Due Nov. 7 PROBLEM 2 Water is sloshing back and forth between two infinite vertical walls separated by a distance L: y Surface Water L h(x,t x Tank The flow is assumed to be

### PRINCIPLES OF FLIGHT

1 Considering a positive cambered aerofoil, the pitching moment when Cl=0 is: A infinite B positive (nose-up). C negative (nose-down). D equal to zero. 2 The angle between the aeroplane longitudinal axis

### Lecture 7 Boundary Layer

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

### AAE 333 Final Exam. Dec Open Book, 1 Crib sheet allowed

AAE 333 Final Exam Dec 16 2009 Open Book, 1 Crib sheet allowed The right answer is worth 5 points. A wrong answer is worth 0. Fill in the circle on the scantron sheet corresponding to your answer chosen

### Theory of turbo machinery. Chapter 3

Theory of turbo machinery Chapter 3 D cascades Let us first understand the facts and then we may seek the causes. (Aristotle) D cascades High hub-tip ratio (of radii) negligible radial velocities D cascades

### Aerodynamics SYST 460/560. George Mason University Fall 2008 CENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCH. Copyright Lance Sherry (2008)

Aerodynamics SYST 460/560 George Mason University Fall 2008 1 CENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCH Copyright Lance Sherry (2008) Ambient & Static Pressure Ambient Pressure Static Pressure 2 Ambient

### Detailed Outline, M E 320 Fluid Flow, Spring Semester 2015

Detailed Outline, M E 320 Fluid Flow, Spring Semester 2015 I. Introduction (Chapters 1 and 2) A. What is Fluid Mechanics? 1. What is a fluid? 2. What is mechanics? B. Classification of Fluid Flows 1. Viscous

### Q. 1 Q. 25 carry one mark each.

GATE 015 Q. 1 Q. 5 carry one mark each. Q.1 The partial differential equation (A) linear and first order (C) non-linear and first order u u + = 0 is t x (B) linear and second order (D) non-linear and second

### Aerodynamics. High-Lift Devices

High-Lift Devices Devices to increase the lift coefficient by geometry changes (camber and/or chord) and/or boundary-layer control (avoid flow separation - Flaps, trailing edge devices - Slats, leading

### Detailed Outline, M E 521: Foundations of Fluid Mechanics I

Detailed Outline, M E 521: Foundations of Fluid Mechanics I I. Introduction and Review A. Notation 1. Vectors 2. Second-order tensors 3. Volume vs. velocity 4. Del operator B. Chapter 1: Review of Basic

### Ethirajan Rathakrishnan. Theoretical Aerodynamics

Ethirajan Rathakrishnan Theoretical Aerodynamics THEORETICAL AERODYNAMICS THEORETICAL AERODYNAMICS Ethirajan Rathakrishnan Indian Institute of Technology Kanpur, India This edition first published 2013

### 1. (20 pts total 2pts each) - Circle the most correct answer for the following questions.

ME 50 Gas Dynamics Spring 009 Final Exam NME:. (0 pts total pts each) - Circle the most correct answer for the following questions. i. normal shock propagated into still air travels with a speed (a) equal

### External Flow and Boundary Layer Concepts

1 2 Lecture (8) on Fayoum University External Flow and Boundary Layer Concepts By Dr. Emad M. Saad Mechanical Engineering Dept. Faculty of Engineering Fayoum University Faculty of Engineering Mechanical

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

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

### 3.1 Definition Physical meaning Streamfunction and vorticity The Rankine vortex Circulation...

Chapter 3 Vorticity Contents 3.1 Definition.................................. 19 3.2 Physical meaning............................. 19 3.3 Streamfunction and vorticity...................... 21 3.4 The Rankine

### Introduction to Aerospace Engineering

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

### Final 1. (25) 2. (10) 3. (10) 4. (10) 5. (10) 6. (10) TOTAL = HW = % MIDTERM = % FINAL = % COURSE GRADE =

MAE101B: Advanced Fluid Mechanics Winter Quarter 2017 http://web.eng.ucsd.edu/~sgls/mae101b_2017/ Name: Final This is a three hour open-book exam. Please put your name on the top sheet of the exam. Answer

### Introduction to Flight Dynamics

Chapter 1 Introduction to Flight Dynamics Flight dynamics deals principally with the response of aerospace vehicles to perturbations in their flight environments and to control inputs. In order to understand

### R09. d water surface. Prove that the depth of pressure is equal to p +.

Code No:A109210105 R09 SET-1 B.Tech II Year - I Semester Examinations, December 2011 FLUID MECHANICS (CIVIL ENGINEERING) Time: 3 hours Max. Marks: 75 Answer any five questions All questions carry equal

### Part A: 1 pts each, 10 pts total, no partial credit.

Part A: 1 pts each, 10 pts total, no partial credit. 1) (Correct: 1 pt/ Wrong: -3 pts). The sum of static, dynamic, and hydrostatic pressures is constant when flow is steady, irrotational, incompressible,

### Air Loads. Airfoil Geometry. Upper surface. Lower surface

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

### External Forced Convection. Copyright The McGraw-Hill Companies, Inc. Permission required for reproduction or display.

External Forced Convection Copyright The McGraw-Hill Companies, Inc. Permission required for reproduction or display. Drag and Heat Transfer in External flow Fluid flow over solid bodies is responsible

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

Stability and Control Some Characteristics of Lifting Surfaces, and Pitch-Moments The lifting surfaces of a vehicle generally include the wings, the horizontal and vertical tail, and other surfaces such

### THE ROLE OF LOCALIZED ROUGHNESS ON THE LAMINAR-TURBULENT TRANSITION ON THE OBLIQUE WING

THE ROLE OF LOCALIZED ROUGHNESS ON THE LAMINAR-TURBULENT TRANSITION ON THE OBLIQUE WING S.N. Tolkachev*, V.N. Gorev*, V.V. Kozlov* *Khristianovich Institute of Theoretical and Applied Mechanics SB RAS

### Chapter 9 Flow over Immersed Bodies

57:00 Mechanics of Fluids and Transport Processes Chapter 9 Professor Fred Stern Fall 009 1 Chapter 9 Flow over Immersed Bodies Fluid flows are broadly categorized: 1. Internal flows such as ducts/pipes,

### Fundamentals of Fluid Dynamics: Ideal Flow Theory & Basic Aerodynamics

Fundamentals of Fluid Dynamics: Ideal Flow Theory & Basic Aerodynamics Introductory Course on Multiphysics Modelling TOMASZ G. ZIELIŃSKI (after: D.J. ACHESON s Elementary Fluid Dynamics ) bluebox.ippt.pan.pl/

### E80. Fluid Measurement The Wind Tunnel Lab. Experimental Engineering.

Fluid Measurement The Wind Tunnel Lab http://twistedsifter.com/2012/10/red-bull-stratos-space-jump-photos/ Feb. 13, 2014 Outline Wind Tunnel Lab Objectives Why run wind tunnel experiments? How can we use

### Masters in Mechanical Engineering. Problems of incompressible viscous flow. 2µ dx y(y h)+ U h y 0 < y < h,

Masters in Mechanical Engineering Problems of incompressible viscous flow 1. Consider the laminar Couette flow between two infinite flat plates (lower plate (y = 0) with no velocity and top plate (y =

### ME332 FLUID MECHANICS LABORATORY (PART I)

ME332 FLUID MECHANICS LABORATORY (PART I) Mihir Sen Department of Aerospace and Mechanical Engineering University of Notre Dame Notre Dame, IN 46556 Version: January 14, 2002 Contents Unit 1: Hydrostatics

### Unsteady Aerodynamic Vortex Lattice of Moving Aircraft. Master thesis

Unsteady Aerodynamic Vortex Lattice of Moving Aircraft September 3, 211 Master thesis Author: Enrique Mata Bueso Supervisors: Arthur Rizzi Jesper Oppelstrup Aeronautical and Vehicle engineering department,

### Numerical Investigation of Laminar Flow over a Rotating Circular Cylinder

International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS Vol:13 No:3 32 Numerical Investigation of Laminar Flow over a Rotating Circular Cylinder Ressan Faris Al-Maliky Department of