a) Derive general expressions for the stream function Ψ and the velocity potential function φ for the combined flow. [12 Marks]
|
|
- Arleen Hudson
- 5 years ago
- Views:
Transcription
1 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 of velocity U in the x-direction. a) Derive general exressions for the stream function Ψ and the velocity otential function φ for the combined flow. [1 Marks] b) Sketch the streamline attern for the combined flow, and state what kind of flow might be redicted by this model. c) In a secific instance, the uniform velocity comonent U=3.0m/s, the strength of the vortex K=7.0m /s and the density of the fluid is ρ =1000kg/m 3. Calculate the ressure difference between a oint on the ositive x-axis and a oint on the ositive y-axis, each 0.5m from the origin. (Assume gravity acts in the z-axis). [8 Marks] Page 1 of 7 AE303 Aerodynamics May 05.doc
2 Question Thin aerofoil theory shows that the vortex strength distribution reresenting a symmetrical aerofoil is: γ = α U ( 1 cosθ ) sinθ where θ is related to x by x=(c/)(1-cosθ ), and non-dimensional load distribution is given by C P = γ/u. a) Integrate the load distribution to show that the lift coefficient, C L, is given by C L =πα, and the itching moment about the leading edge, Cm LE, is given by Cm LE =-πα/. [15 Marks] b) Obtain an exression for C P in terms of x, and sketch the load distribution commenting on the values at the leading and trailing edges. [8 Marks] c) Comment on the alicability of thin aerofoil theory, and the limitations of the method. [ Marks] Page of 7 AE303 Aerodynamics May 05.doc
3 Question 3 For a finite san wing: a) Describe how the lift and drag forces generated by a finite san wing differ from the theoretical case of an infinite san wing, and the hysical mechanism for these differences. b) A wing can be reresented by two horseshoe vortices as shown below in figure Q3. 0.b Γ/4 b 0.3b 3Γ/4 c By calculating the downwash at the oint and relating the geometric and effective incidences at that oint, show that the lift-curve sloe is given by: dc L dα πar = AR where AR is the asect ratio. [18 Marks] c) Comment on the significance of the value of dc L /dα when AR. [ Marks] Page 3 of 7 AE303 Aerodynamics May 05.doc
4 Question 4 An air flow at Mach number.5 and ressure 50 kn/m enters a divergent section of a duct having an inlet area of 50mm. A normal shock occurs at the exit where the Mach number is 4.0 and the temerature immediately ustream of the shock is 10K. a) Determine the mass flow rate, the exit area of the duct and the air ressure immediately downstream of the shock. [18 Marks] b) Sketch the general trends of ressure, temerature, density, velocity and Mach number, total ressure and total temerature through the divergent duct. Assume reversible adiabatic flow, other than through the shock. [9 Marks] The following equations may be used, where aroriate, and the tye of each equation used must be stated, e.g: steady flow continuity equation. 1 T = T 1 γ ( γ 1) γ 1 T 1 + M = constant ( 1 + γm ) = constant M = + γm1 ( γ 1) M1 ( γ 1) Page 4 of 7 AE303 Aerodynamics May 05.doc
5 Question 5 The suersonic flow ast a wedge bilane wing is shown in figure Q5 below. A l α α B M h C α D α E a) Comlete the sketch the suersonic flow field (drawing in your exam work book) by adding all the other waves emanating from oints ABCD and E and label them as shock or exansion waves. Also draw some streamlines above, between and below the wings. b) Using linearised (Ackeret) theory, find the lift and drag coefficients (based on the area of one wing) and the lift to drag ratio, in terms of wedge angle, α, and free stream Mach number, M, for the bilane wing. State all assumtions in Ackeret s theory. [8 Marks] c) Calculate the correct sacing, h, for the wings in terms of the free stream Mach number and the dimension, l. [ Marks] d) Assume the wings are now moved further aart so that they do not interfere. Calculate the sacing required to achieve this and the corresonding values of C L and C D. Comment on the merits of the suersonic wedge bilane arrangement. [10 Marks] Page 5 of 7 AE303 Aerodynamics May 05.doc
6 Question 6 Laminar flow occurs ast a flat solid boundary. The velocity distribution may be aroximated by the exression: u U y y = δ δ where u is the velocity at a distance y from the boundary, U is the free stream velocity and δ is the boundary layer thickness. a) Show that this distribution satisfies the boundary requirements for a boundary layer. b) Show that the boundary layer thickness varies with the distance x from the leading edge of the boundary and the Reynolds number Re x =ρux/µ according to the exression δ = 5.48x(Re x ) -1/ [0 Marks] The following relationshis may be assumed without roof. Local wall shear stress: τ w = ρu dθ dx where the momentum thickness: u θ = δ 1 0 U u dy U Page 6 of 7 AE303 Aerodynamics May 05.doc
7 Question 7 For a turbulent boundary layer flow: a) exlain the following terms, including the equations relating u + and y + : i) laminar sublayer ii) inner layer iii) outer layer Include in your answer a sketch the grah relating u + and y + through a turbulent boundary layer [15 Marks] b) Assuming that for flow through a long engine intake the friction coefficient is given by C F = 4C f = 0.316(Re) -1/4, that the wall shear stress is indeendent of ie radius R and that the ratio of local velocity u to freestream velocity U does not change with freestream velocity, show that: u U 1 y 7 R [10 Marks] Note that: + u u =, u τ y ρu µ + τ y = where wall friction velocity is u τ = τw ρ Examiner : Dr. S. Prince External Examiner : Professor D.I.A. Poll Page 7 of 7 AE303 Aerodynamics May 05.doc
Given a stream function for a cylinder in a uniform flow with circulation: a) Sketch the flow pattern in terms of streamlines.
Question Given a stream function for a cylinder in a uniform flow with circulation: R Γ r ψ = U r sinθ + ln r π R a) Sketch the flow pattern in terms of streamlines. b) Derive an expression for the angular
More informationAE301 Aerodynamics I UNIT A: Fundamental Concepts
AE301 Aerodynamics I UNIT A: Fundamental Concets ROAD MAP... A-1: Engineering Fundamentals Reiew A-: Standard Atmoshere A-3: Goerning Equations of Aerodynamics A-4: Airseed Measurements A-5: Aerodynamic
More informationIntroduction to Aerospace Engineering
Introduction to Aerosace Engineering Lecture slides hallenge the future Introduction to Aerosace Engineering Aerodynamics & Prof. H. Bijl ir. N. Timmer &. Airfoils and finite wings Anderson 5.9 end of
More informationSPC 407 Sheet 6 - Solution Compressible Flow Fanno Flow
SPC 407 Sheet 6 - Solution Comressible Flow Fanno Flow 1. What is the effect of friction on flow velocity in subsonic and suersonic Fanno flow? Friction increases the flow velocity in subsonic Fanno flow,
More informationMestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 2012/13
Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 212/13 Exam 2ª época, 2 February 213 Name : Time : 8: Number: Duration : 3 hours 1 st Part : No textbooks/notes allowed 2 nd Part :
More informationGiven the water behaves as shown above, which direction will the cylinder rotate?
water stream fixed but free to rotate Given the water behaves as shown above, which direction will the cylinder rotate? ) Clockwise 2) Counter-clockwise 3) Not enough information F y U 0 U F x V=0 V=0
More informationConsider a wing of finite span with an elliptic circulation distribution:
Question 1 (a) onsider a wing of finite span with an elliptic circulation distribution: Γ( y) Γo y + b = 1, - s y s where s=b/ denotes the wing semi-span. Use this equation, in conjunction with the Kutta-Joukowsky
More informationMasters in Mechanical Engineering Aerodynamics 1 st Semester 2015/16
Masters in Mechanical Engineering Aerodynamics st Semester 05/6 Exam st season, 8 January 06 Name : Time : 8:30 Number: Duration : 3 hours st Part : No textbooks/notes allowed nd Part : Textbooks allowed
More informationChapter 10: Flow Flow in in Conduits Conduits Dr Ali Jawarneh
Chater 10: Flow in Conduits By Dr Ali Jawarneh Hashemite University 1 Outline In this chater we will: Analyse the shear stress distribution across a ie section. Discuss and analyse the case of laminar
More informationHigh speed wind tunnels 2.0 Definition of high speed. 2.1 Types of high speed wind tunnels
Module Lectures 6 to 1 High Seed Wind Tunnels Keywords: Blow down wind tunnels, Indraft wind tunnels, suersonic wind tunnels, c-d nozzles, second throat diffuser, shocks, condensation in wind tunnels,
More informationf self = 1/T self (b) With revolution, rotaton period T rot in second and the frequency Ω rot are T yr T yr + T day T rot = T self > f self
Problem : Units : Q-a Mathematically exress the relationshi between the different units of the hysical variables: i) Temerature: ) Fahrenheit and Celsius; 2) Fahrenheit and Kelvin ii) Length: ) foot and
More informationFinal 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
More informationTheory of turbomachinery. Chapter 1
Theory of turbomachinery Chater Introduction: Basic Princiles Take your choice of those that can best aid your action. (Shakeseare, Coriolanus) Introduction Definition Turbomachinery describes machines
More informationSPC Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30
SPC 307 - Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30 1. The maximum velocity at which an aircraft can cruise occurs when the thrust available with the engines operating with the
More informationINSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad
INSTITUTE OF AERONAUTICAL ENGINEERING (Autonomous) Dundigal, Hyderabad - 500 043 AERONAUTICAL ENGINEERING TUTORIAL QUESTION BANK Course Name : LOW SPEED AERODYNAMICS Course Code : AAE004 Regulation : IARE
More informationPart 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,
More information16. CHARACTERISTICS OF SHOCK-WAVE UNDER LORENTZ FORCE AND ENERGY EXCHANGE
16. CHARACTERISTICS OF SHOCK-WAVE UNDER LORENTZ FORCE AND ENERGY EXCHANGE H. Yamasaki, M. Abe and Y. Okuno Graduate School at Nagatsuta, Tokyo Institute of Technology 459, Nagatsuta, Midori-ku, Yokohama,
More informationHypersonic flow: introduction
Hyersonic flow: introduction Van Dyke: Hyersonic flow is flow ast a body at high ach number, where nonlinearity is an essential feature of the flow. Also understood, for thin bodies, that if is the thickness-to-chord
More informationModule 4 : Lecture 1 COMPRESSIBLE FLOWS (Fundamental Aspects: Part - I)
Module 4 : Lecture COMPRESSIBLE FLOWS (Fundamental Asects: Part - I) Overview In general, the liquids and gases are the states of a matter that comes under the same category as fluids. The incomressible
More informationSignature: (Note that unsigned exams will be given a score of zero.)
Neatly print your name: Signature: (Note that unsigned exams will be given a score of zero.) Circle your lecture section (-1 point if not circled, or circled incorrectly): Prof. Dabiri Prof. Wassgren Prof.
More informationCompressible Flow Introduction. Afshin J. Ghajar
36 Comressible Flow Afshin J. Ghajar Oklahoma State University 36. Introduction...36-36. he Mach Number and Flow Regimes...36-36.3 Ideal Gas Relations...36-36.4 Isentroic Flow Relations...36-4 36.5 Stagnation
More information(British) (SI) British Metric L T [V] = L T. [a] = 2 [F] = F = 2 T
Hydraulics ecture # CWR 40 age () ecture # Outline: Review of terminology in fluid mechanics: Energy or work Hydraulic head Bernoulli s aw, Conductivity (examle) ransient & turbulent Friction head loss
More informationLaminar 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
More informationDAY 19: Boundary Layer
DAY 19: Boundary Layer flat plate : let us neglect the shape of the leading edge for now flat plate boundary layer: in blue we highlight the region of the flow where velocity is influenced by the presence
More informationCompressible Duct Flow with Friction
Compressible Duct Flow with Friction We treat only the effect of friction, neglecting area change and heat transfer. The basic assumptions are 1. Steady one-dimensional adiabatic flow 2. Perfect gas with
More informationV (r,t) = i ˆ u( x, y,z,t) + ˆ j v( x, y,z,t) + k ˆ w( x, y, z,t)
IV. DIFFERENTIAL RELATIONS FOR A FLUID PARTICLE This chapter presents the development and application of the basic differential equations of fluid motion. Simplifications in the general equations and common
More informationTransport processes. 7. Semester Chemical Engineering Civil Engineering
Transport processes 7. Semester Chemical Engineering Civil Engineering 1. Elementary Fluid Dynamics 2. Fluid Kinematics 3. Finite Control Volume Analysis 4. Differential Analysis of Fluid Flow 5. Viscous
More informationFE Exam Fluids Review October 23, Important Concepts
FE Exam Fluids Review October 3, 013 mportant Concepts Density, specific volume, specific weight, specific gravity (Water 1000 kg/m^3, Air 1. kg/m^3) Meaning & Symbols? Stress, Pressure, Viscosity; Meaning
More informationAerodynamics. Basic Aerodynamics. Continuity equation (mass conserved) Some thermodynamics. Energy equation (energy conserved)
Flow with no friction (inviscid) Aerodynamics Basic Aerodynamics Continuity equation (mass conserved) Flow with friction (viscous) Momentum equation (F = ma) 1. Euler s equation 2. Bernoulli s equation
More informationSimplifications to Conservation Equations
Chater 5 Simlifications to Conservation Equations 5.1 Steady Flow If fluid roerties at a oint in a field do not change with time, then they are a function of sace only. They are reresented by: ϕ = ϕq 1,
More informationτ du In his lecture we shall look at how the forces due to momentum changes on the fluid and viscous forces compare and what changes take place.
4. Real fluids The flow of real fluids exhibits viscous effect, that is they tend to stick to solid surfaces and have stresses within their body. You might remember from earlier in the course Newtons law
More informationDrag (2) Induced Drag Friction Drag Form Drag Wave Drag
Drag () Induced Drag Friction Drag Form Drag Wave Drag Outline Nomenclature and Concepts Farfield Drag Analysis Induced Drag Multiple Lifting Surfaces Zero Lift Drag :Friction and Form Drag Supersonic
More informationChapter 6. Thermodynamics and the Equations of Motion
Chater 6 hermodynamics and the Equations of Motion 6.1 he first law of thermodynamics for a fluid and the equation of state. We noted in chater 4 that the full formulation of the equations of motion required
More information7.6 Example von Kármán s Laminar Boundary Layer Problem
CEE 3310 External Flows (Boundary Layers & Drag, Nov. 11, 2016 157 7.5 Review Non-Circular Pipes Laminar: f = 64/Re DH ± 40% Turbulent: f(re DH, ɛ/d H ) Moody chart for f ± 15% Bernoulli-Based Flow Metering
More informationPART 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
More information1. Fluid Dynamics Around Airfoils
1. Fluid Dynamics Around Airfoils Two-dimensional flow around a streamlined shape Foces on an airfoil Distribution of pressue coefficient over an airfoil The variation of the lift coefficient with the
More informationMasters 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 =
More informationAirfoils and Wings. Eugene M. Cliff
Airfoils and Wings Eugene M. Cliff 1 Introduction The primary purpose of these notes is to supplement the text material related to aerodynamic forces. We are mainly interested in the forces on wings and
More informationSignature: (Note that unsigned exams will be given a score of zero.)
Neatly print your name: Signature: (Note that unsigned exams will be given a score of zero.) Circle your lecture section (-1 point if not circled, or circled incorrectly): Prof. Dabiri Prof. Wassgren Prof.
More informationIII. Flow Around Bends: Meander Evolution
III. Flow Around Bends: Meander Evolution 1. Introduction Hooke (1975) [aer available] first detailed data and measurements about what haens around meander bends how flow velocity and shear stress fields
More informationExternal 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
More informationChapter 5 Mass, Momentum, and Energy Equations
57:00 Mechanics of Fluids and Transort Processes Chater 5 Professor Fred Stern Fall 006 Chater 5 Mass, Momentum, and Energy Equations Flow Rate and Conservation of Mass. cross-sectional area oriented normal
More informationSteady, 1-d, constant area, adiabatic flow with no external work but with friction Conserved quantities
School of Aerosace Engineering Stead, -d, constant area, adiabatic flow with no external work but with friction Conserved quantities since adiabatic, no work: h o constant since Aconst: mass fluxρvconstant
More informationFigure 3: Problem 7. (a) 0.9 m (b) 1.8 m (c) 2.7 m (d) 3.6 m
1. For the manometer shown in figure 1, if the absolute pressure at point A is 1.013 10 5 Pa, the absolute pressure at point B is (ρ water =10 3 kg/m 3, ρ Hg =13.56 10 3 kg/m 3, ρ oil = 800kg/m 3 ): (a)
More informationDrag Computation (1)
Drag Computation (1) Why drag so concerned Its effects on aircraft performances On the Concorde, one count drag increase ( C D =.0001) requires two passengers, out of the 90 ~ 100 passenger capacity, be
More informationEfficiencies. Damian Vogt Course MJ2429. Nomenclature. Symbol Denotation Unit c Flow speed m/s c p. pressure c v. Specific heat at constant J/kgK
Turbomachinery Lecture Notes 1 7-9-1 Efficiencies Damian Vogt Course MJ49 Nomenclature Subscrits Symbol Denotation Unit c Flow seed m/s c Secific heat at constant J/kgK ressure c v Secific heat at constant
More informationAerodynamics. 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
More informationThe E80 Wind Tunnel Experiment the experience will blow you away. by Professor Duron Spring 2012
The E80 Wind Tunnel Experiment the experience will blow you away by Professor Duron Spring 2012 Objectives To familiarize the student with the basic operation and instrumentation of the HMC wind tunnel
More informationNotes on pressure coordinates Robert Lindsay Korty October 1, 2002
Notes on ressure coordinates Robert Lindsay Korty October 1, 2002 Obviously, it makes no difference whether the quasi-geostrohic equations are hrased in height coordinates (where x, y,, t are the indeendent
More informationFLUID MECHANICS. Atmosphere, Ocean. Aerodynamics. Energy conversion. Transport of heat/other. Numerous industrial processes
SG2214 Anders Dahlkild Luca Brandt FLUID MECHANICS : SG2214 Course requirements (7.5 cr.) INL 1 (3 cr.) 3 sets of home work problems (for 10 p. on written exam) 1 laboration TEN1 (4.5 cr.) 1 written exam
More informationFluid Mechanics Qualifying Examination Sample Exam 2
Fluid Mechanics Qualifying Examination Sample Exam 2 Allotted Time: 3 Hours The exam is closed book and closed notes. Students are allowed one (double-sided) formula sheet. There are five questions on
More informationActive Control of Separated Cascade Flow
Chapter 5 Active Control of Separated Cascade Flow In this chapter, the possibility of active control using a synthetic jet applied to an unconventional axial stator-rotor arrangement is investigated.
More informationProf. Scalo Prof. Vlachos Prof. Ardekani Prof. Dabiri 08:30 09:20 A.M 10:30 11:20 A.M. 1:30 2:20 P.M. 3:30 4:20 P.M.
Page 1 Neatly print your name: Signature: (Note that unsigned exams will be given a score of zero.) Circle your lecture section (-1 point if not circled, or circled incorrectly): Prof. Scalo Prof. Vlachos
More informationMET 4302 Midterm Study Guide 19FEB18
The exam will be 4% short answer and the remainder (6%) longer (1- aragrahs) answer roblems and mathematical derivations. The second section will consists of 6 questions worth 15 oints each. Answer 4.
More informationWater 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
More informationOptimisation of Pressure Loss and Flow Distribution at Pipe Bifurcation
ISSN 9 86 Volume, Issue 9 Setember 07 Otimisation of Pressure Loss and Flow Distribution at Pie Bifurcation Dr. Nagaraj Sitaram Professor, Deartment of Civil Engineering,School of Engineering Technology,
More informationFundamental Concepts of Convection : Flow and Thermal Considerations. Chapter Six and Appendix D Sections 6.1 through 6.8 and D.1 through D.
Fundamental Concepts of Convection : Flow and Thermal Considerations Chapter Six and Appendix D Sections 6.1 through 6.8 and D.1 through D.3 6.1 Boundary Layers: Physical Features Velocity Boundary Layer
More informationFlight Vehicle Terminology
Flight Vehicle Terminology 1.0 Axes Systems There are 3 axes systems which can be used in Aeronautics, Aerodynamics & Flight Mechanics: Ground Axes G(x 0, y 0, z 0 ) Body Axes G(x, y, z) Aerodynamic Axes
More informationR09. 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
More informationFLUID 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
More information58:160 Intermediate Fluid Mechanics Bluff Body Professor Fred Stern Fall 2014
Professor Fred Stern Fall 04 Chapter 7 Bluff Body Fluid flows are broadly categorized:. Internal flows such as ducts/pipes, turbomachinery, open channel/river, which are bounded by walls or fluid interfaces:
More informationChapter 9. Flow over Immersed Bodies
Chapter 9 Flow over Immersed Bodies We consider flows over bodies that are immersed in a fluid and the flows are termed external flows. We are interested in the fluid force (lift and drag) over the bodies.
More informationOffshore Hydromechanics Module 1
Offshore Hydromechanics Module 1 Dr. ir. Pepijn de Jong 4. Potential Flows part 2 Introduction Topics of Module 1 Problems of interest Chapter 1 Hydrostatics Chapter 2 Floating stability Chapter 2 Constant
More informationDetailed 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
More informationHigh Speed Aerodynamics. Copyright 2009 Narayanan Komerath
Welcome to High Speed Aerodynamics 1 Lift, drag and pitching moment? Linearized Potential Flow Transformations Compressible Boundary Layer WHAT IS HIGH SPEED AERODYNAMICS? Airfoil section? Thin airfoil
More information1. 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
More informationFall 2014 Qualifying Exam Thermodynamics Closed Book
Fall 2014 Qualifying Exam Thermodynamics Closed Book Saturated ammonia vapor at 200 O F flows through a 0.250 in diameter tube. The ammonia passes through a small orifice causing the pressure to drop very
More informationChapter 6: Incompressible Inviscid Flow
Chapter 6: Incompressible Inviscid Flow 6-1 Introduction 6-2 Nondimensionalization of the NSE 6-3 Creeping Flow 6-4 Inviscid Regions of Flow 6-5 Irrotational Flow Approximation 6-6 Elementary Planar Irrotational
More informationS.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
More informationFundamentals of Aerodynamics
Fundamentals of Aerodynamics Fourth Edition John D. Anderson, Jr. Curator of Aerodynamics National Air and Space Museum Smithsonian Institution and Professor Emeritus University of Maryland Me Graw Hill
More informationRandom Problems. Problem 1 (30 pts)
Random Problems Problem (3 pts) An untwisted wing with an elliptical planform has an aspect ratio of 6 and a span of m. The wing loading (defined as the lift per unit area of the wing) is 9N/m when flying
More informationWeek 8 lectures. ρ t +u ρ+ρ u = 0. where µ and λ are viscosity and second viscosity coefficients, respectively and S is the strain tensor:
Week 8 lectures. Equations for motion of fluid without incomressible assumtions Recall from week notes, the equations for conservation of mass and momentum, derived generally without any incomressibility
More informationNumerical and Experimental Study on the Effect of Guide Vane Insertion on the Flow Characteristics in a 90º Rectangular Elbow
Numerical and Experimental Study on the Effect of Guide Vane Insertion on the Flow Characteristics in a 90º Rectangular Elbow Sutardi 1, Wawan A. W., Nadia, N. and Puspita, K. 1 Mechanical Engineering
More informationFluid Mechanics II. Newton s second law applied to a control volume
Fluid Mechanics II Stead flow momentum equation Newton s second law applied to a control volume Fluids, either in a static or dnamic motion state, impose forces on immersed bodies and confining boundaries.
More informationCHAPTER 4 BOUNDARY LAYER FLOW APPLICATION TO EXTERNAL FLOW
CHAPTER 4 BOUNDARY LAYER FLOW APPLICATION TO EXTERNAL FLOW 4.1 Introduction Boundary layer concept (Prandtl 1904): Eliminate selected terms in the governing equations Two key questions (1) What are the
More informationAEROSPACE ENGINEERING DEPARTMENT. Second Year - Second Term ( ) Fluid Mechanics & Gas Dynamics
AEROSPACE ENGINEERING DEPARTMENT Second Year - Second Term (2008-2009) Fluid Mechanics & Gas Dynamics Similitude,Dimensional Analysis &Modeling (1) [7.2R*] Some common variables in fluid mechanics include:
More informationChapter 7 Energy Principle
Chater 7: Energy Princile By Dr Ali Jawarneh Hashemite University Outline In this chater we will: Derive and analyse the Energy equation. Analyse the flow and shaft work. Derive the equation for steady
More informationConvection in Three-Dimensional Separated and Attached Flow
Convection in Three-Dimensional Separated and Attached Flow B. F. Armaly Convection Heat Transfer Laboratory Department of Mechanical and Aerospace Engineering, and Engineering Mechanics University of
More informationNUMERICAL ANALYSIS OF THE IMPACT OF THE INLET AND OUTLET JETS FOR THE THERMAL STRATIFICATION INSIDE A STORAGE TANK
NUMERICAL ANALYSIS OF HE IMAC OF HE INLE AND OULE JES FOR HE HERMAL SRAIFICAION INSIDE A SORAGE ANK A. Zachár I. Farkas F. Szlivka Deartment of Comuter Science Szent IstvÆn University Æter K. u.. G d llı
More information9.3 Laminar Flat-Plate Boundary Layer: Exact Solution w-19
9.3 Laminar Flat-Plate Boundary Layer: Exact Solution w-19 Laminar Flat-Plate Boundary Layer: Exact Solution The solution for the laminar boundary layer on a horizontal flat late was obtained by Prtl s
More information2 Navier-Stokes Equations
1 Integral analysis 1. Water enters a pipe bend horizontally with a uniform velocity, u 1 = 5 m/s. The pipe is bended at 90 so that the water leaves it vertically downwards. The input diameter d 1 = 0.1
More informationFE FORMULATIONS FOR PLASTICITY
G These slides are designed based on the book: Finite Elements in Plasticity Theory and Practice, D.R.J. Owen and E. Hinton, 1970, Pineridge Press Ltd., Swansea, UK. 1 Course Content: A INTRODUCTION AND
More informationFundamentals of Aerodynamits
Fundamentals of Aerodynamits Fifth Edition in SI Units John D. Anderson, Jr. Curator of Aerodynamics National Air and Space Museum Smithsonian Institution and Professor Emeritus University of Maryland
More informationFluid Dynamics Exercises and questions for the course
Fluid Dynamics Exercises and questions for the course January 15, 2014 A two dimensional flow field characterised by the following velocity components in polar coordinates is called a free vortex: u r
More informationMAE 222 Mechanics of Fluids Final Exam with Answers January 13, Give succinct answers to the following word questions.
MAE 222 Mechanics of Fluids Final Exam with Answers January 13, 1994 Closed Book Only, three hours: 1:30PM to 4:30PM 1. Give succinct answers to the following word questions. (a) Why is dimensional analysis
More informationChapter 1 Fundamentals
Chater Fundamentals. Overview of Thermodynamics Industrial Revolution brought in large scale automation of many tedious tasks which were earlier being erformed through manual or animal labour. Inventors
More informationGT NUMERICAL STUDY OF A CASCADE UNSTEADY SEPARATION FLOW
Proceedings of ASME urbo Exo 2004 2004 Power for Land, Sea, and Air Vienna, Austria, June 4-7, 2004 G2004-5395 NUMERICAL SUDY OF A CASCADE UNSEADY SEPARAION FLOW Zongjun Hu and GeCheng Zha Deartment of
More informationESCI 342 Atmospheric Dynamics I Lesson 10 Vertical Motion, Pressure Coordinates
Reading: Martin, Section 4.1 PRESSURE COORDINATES ESCI 342 Atmosheric Dynamics I Lesson 10 Vertical Motion, Pressure Coordinates Pressure is often a convenient vertical coordinate to use in lace of altitude.
More informationUniversity of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005
University of California at Berkeley Department of Mechanical Engineering ME 163 ENGINEERING AERODYNAMICS FINAL EXAM, 13TH DECEMBER 2005 Answer both questions. Question 1 is worth 30 marks and question
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 3-0-0 Introduction to Aerospace Engineering Aerodynamics 5 & 6 Prof. H. Bijl ir. N. Timmer Delft University of Technology 5. Compressibility
More information1. 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
More information6.1 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
More informationPrinciples of Convection
Principles of Convection Point Conduction & convection are similar both require the presence of a material medium. But convection requires the presence of fluid motion. Heat transfer through the: Solid
More informationLiquid water static energy page 1/8
Liquid water static energy age 1/8 1) Thermodynamics It s a good idea to work with thermodynamic variables that are conserved under a known set of conditions, since they can act as assive tracers and rovide
More informationConsider a control volume in the form of a straight section of a streamtube ABCD.
6 MOMENTUM EQUATION 6.1 Momentum and Fluid Flow In mechanics, the momentum of a particle or object is defined as the product of its mass m and its velocity v: Momentum = mv The particles of a fluid stream
More informationLecture 7 Boundary Layer
SPC 307 Introduction to Aerodynamics Lecture 7 Boundary Layer April 9, 2017 Sep. 18, 2016 1 Character of the steady, viscous flow past a flat plate parallel to the upstream velocity Inertia force = ma
More informationA NEW STREAMLINE CURVATURE THROUGHFLOW METHOD FOR RADIAL TURBOMACHINERY
Proceedings of ASME Turbo Exo 008: Power for Land, Sea and Air GT008 June 9-3, 008, Berlin, Germany GT008-5087 A NEW STREAMLINE CURVATURE THROUGHFLOW METHOD FOR RADIAL TURBOMACHINERY Michael Casey ITSM
More informationAE301 Aerodynamics I UNIT A: Fundamental Concepts
AE3 Aerodynamics I UNIT A: Fundamental Concets ROAD MAP... A-: Engineering Fundamentals Review A-: Standard Atmoshere A-3: Governing Equations of Aerodynamics A-4: Airseed Measurements A-5: Aerodynamic
More informationVisualization of flow pattern over or around immersed objects in open channel flow.
EXPERIMENT SEVEN: FLOW VISUALIZATION AND ANALYSIS I OBJECTIVE OF THE EXPERIMENT: Visualization of flow pattern over or around immersed objects in open channel flow. II THEORY AND EQUATION: Open channel:
More informationFluid Mechanics. Chapter 9 Surface Resistance. Dr. Amer Khalil Ababneh
Fluid Mechanics Chapter 9 Surface Resistance Dr. Amer Khalil Ababneh Wind tunnel used for testing flow over models. Introduction Resistances exerted by surfaces are a result of viscous stresses which create
More information