OUTLINE FOR Chapter 3
|
|
|
- Frederick Watkins
- 5 years ago
- Views:
Transcription
1 013/4/ OUTLINE FOR Chapter 3 AERODYNAMICS (W-1-1 BERNOULLI S EQUATION & integration BERNOULLI S EQUATION AERODYNAMICS (W-1-1
2 013/4/ BERNOULLI S EQUATION FOR AN IRROTATION FLOW AERODYNAMICS (W-1-.1 VENTURI TUBE AERODYNAMICS (W-1-3
3 013/4/ PITOT-STATIC TUBE for susonic compressile flow (see Ch8 for detail for supersonic compressile flow (see Ch8 for detail AERODYNAMICS (W_1_4 Pressure coefficient: PRESSURE COEFFICIENT C p AERODYNAMICS (W_1_5 3
4 013/4/ REVIEW FOR IRROTATIONAL, INCOMPRESSIBLE FLOW: Continuit equation Momentum equation Irrotational flow = 0 GOVERNING EQUATION FOR IRROTATIONAL, INCOMPRESSIBLE FLOW: LAPLACE S EQUATION Continuit equation Incompressile: constant For incompressile flow: there eists a streamfunction For irrotational flow: there eists a velocit potential Laplace s equation For irrotational, incompressile flow: Laplace s equation For irrotational, incompressile flow, there are velocit potential ti and streamfunction ti that oth satisf Laplace s equation. 0 0 AERODYNAMICS (W_1_6 4
5 013/4/ LAPLACE S EQUATION Laplace s equation is a second-order linear partial differential equation. If 1,, 3,, n represent n separate solutions of Laplace s equation, then = n is also a solution of Laplace s equation Boundar Conditions: Infinite oundar conditions: Wall oundar conditions: or or AERODYNAMICS (W-1-7 SUMMARY AERODYNAMICS (W-1-8 5
6 013/4/ OUTLINE FOR Chapter 3 AERODYNAMICS (W--1 LAPLACE S EQUATION: GOVERNING EQUATION FOR IRROTATIONAL, INCOMPRESSIBLE FLOW Some elementar flows: Laplace s equation is a second-order linear partial differential equation. If 1,, 3,, n represent n separate solutions of Laplace s equation, then = n is also a solution of Laplace s equation. Therefore, the solution of a comple flow are usuall in the form of a sum of elementar flow solutions. Uniform flow (1st elementar flow Source and Sink (nd elementar flow Comine Uniform flow with a Source and Sink. Doulet flow (3rd elementar flow Comine Uniform flow with a Doulet. Vorte flow (4th elementar flow Comine Uniform flow with Doulet and Vorte flows AERODYNAMICS (W-- 6
7 013/4/ 1st ELEMENTARY FLOW - UNIFORM FLOW Velocit potential Cartesian coordinates Basic Flow u = V v = 0 Satisf incompressile flow Satisf irrotational flow Stream function Cartesian coordinates or Clinderical coordinates AERODYNAMICS (W--3 nd ELEMENTARY FLOW - SOURCE & SINK FLOW Basic flow: Stif Satisf = 0 Satisf incompressile flow = 0 irrotational flow Velocit potential Polar coordinates Stream function Polar coordinates AERODYNAMICS (W--4 7
8 013/4/ THE COMBINATION OF A UNIFORM FLOW WITH A SOURCE - THE SEMI-INFINITE BODY W= /V Stagnation point: Stagnation streamline: 0 Width of semi-infinite od: r sin (1 V 1 W ( 00 V W= /V AERODYNAMICS (W--5 THE PRESSURE DISTRIBUTION OVER THE SEMI-INFINITE BODY Pressure coefficient: Stream function: Streamline equation of the surface: 1 V Vr V ( V cos ( V sin V (cos sin ( V cos ( r 4 r r r o r V V o (r V r V V V o ( V cos ( o 4 r r V r r 1 o (cos ( o V r r V r r C 1 [ o (cos ( o P ] V r r AERODYNAMICS (W--6 8
9 013/4/ 9 THE COMBINATION OF A UNIFORM FLOW WITH A SOURCE AND SINK - THE RANKINE OVAL ln( ln( r 1 r V ( ln( ( ln( V ln(( ln(( V Stagnation points: ( ( V u ln(( 4 ln(( 4 V ( ( v 0 ( ( V u 0 v AERODYNAMICS (W--7 Stagnation streamline: 0 ( ( v =0 V DOUBLET FLOW AERODYNAMICS (W--8
10 013/4/ NONLIFTING FLOW OVER A CIRCULAR CYLINDER Velocit Field: On the surface of the clinder Stagnation points and streamline: Circle with radius AERODYNAMICS (W--9 PRESSURE COEEFICIENT DISTRBUTION OVER THE SURFACE OF A CIRCULAR CYLINDER Pressure coefficient: On the surface of the clinder = 0 = 0 = 0 = 0 L (lift = D (drag = 0 AERODYNAMICS (W
11 013/4/ OUTLINE FOR Chapter 3 AERODYNAMICS (W-3-1 4th ELEMENTARY FLOW - VORTEX FLOW Basic Flow 0 = 0 incompressile flow = 0 Velocit potential irrotational flow ecept the origin What happens at r=0? Stream function AERODYNAMICS (W-3-11
12 013/4/ LIFTING FLOW OVER A CIRCULAR CYLINDER Velocit Field: Stagnation points: On the surface of the clinder AERODYNAMICS (W-3-3 PRESSURE COEEFICIENT DISTRBUTION OVER THE SURFACE OF A LIFTING CIRCULAR CYLINDER On the surface of the clinder Pressure coefficient: Drag coefficient: = C a D (drag = 0 AERODYNAMICS (W-3-4 1
13 013/4/ LIFT CREATION ON A SPINNING CIRCULAR CYLINDER Lift: = C n Creation of lift on a spinning clinder AERODYNAMICS (W-3-5 on the surface of the clinder. Stream function for a lifting flow over a circular clinder On the surface of the clinder r=r = 0 =-V sin - /(R Peak (negative pressure coefficient appears at =/ = 1-(- - /(RV( = 5 C p = 1-(- - 5/( = -6.8 AERODYNAMICS (W
14 013/4/ =5 Point B AERODYNAMICS (W-3-5. KUTTA JOUKOWSKI THEOREM For a closed two-dimensional od of aritrar shape, the lift per unit span is L = V AERODYNAMICS (W
15 013/4/ SUMMARY UNIFORM FLOW SOURCE & SINK DOUBLET VORTEX AERODYNAMICS (W-3-7 Source Panel Method (I ds ds d ln r 15
16 013/4/ Source Panel Method (II Source Panel Method (III 16
17 013/4/ Source Panel Method (IV Source Panel Method (V 17
18 013/4/ Source Panel Method (VI Source Panel Method (VII 18
19 013/4/ Source Panel Method (VIII Source Panel Method (IX 19
20 013/4/ Source Panel Method (X 0
21 013/4/ 1
22 013/4/ sucritical supercritical
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
Offshore 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
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
Method of Images
. - Marine Hdrodnamics, Spring 5 Lecture 11. - Marine Hdrodnamics Lecture 11 3.11 - Method of Images m Potential for single source: φ = ln + π m ( ) Potential for source near a wall: φ = m ln +( ) +ln
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
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
General Solution of the Incompressible, Potential Flow Equations
CHAPTER 3 General Solution of the Incompressible, Potential Flow Equations Developing the basic methodology for obtaining the elementary solutions to potential flow problem. Linear nature of the potential
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
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
Chapter 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
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
AE301 Aerodynamics I UNIT B: Theory of Aerodynamics
AE301 Aerodynamics I UNIT B: Theory of Aerodynamics ROAD MAP... B-1: Mathematics for Aerodynamics B-: Flow Field Representations B-3: Potential Flow Analysis B-4: Applications of Potential Flow Analysis
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
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
Exercise 9, Ex. 6.3 ( submarine )
Exercise 9, Ex. 6.3 ( submarine The flow around a submarine moving at at velocity V can be described by the flow caused by a source and a sink with strength Q at a distance a from each other. V x Submarine
Marine Hydrodynamics Prof.TrilochanSahoo Department of Ocean Engineering and Naval Architecture Indian Institute of Technology, Kharagpur
Marine Hydrodynamics Prof.TrilochanSahoo Department of Ocean Engineering and Naval Architecture Indian Institute of Technology, Kharagpur Lecture - 10 Source, Sink and Doublet Today is the tenth lecture
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
Copyright 2007 N. Komerath. Other rights may be specified with individual items. All rights reserved.
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
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
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
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
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/
Exercise 9: Model of a Submarine
Fluid Mechanics, SG4, HT3 October 4, 3 Eample : Submarine Eercise 9: Model of a Submarine The flow around a submarine moving at a velocity V can be described by the flow caused by a source and a sink with
PART II: 2D Potential Flow
AERO301:Spring2011 II(a):EulerEqn.& ω = 0 Page1 PART II: 2D Potential Flow II(a): Euler s Equation& Irrotational Flow We have now completed our tour through the fundamental conservation laws that apply
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
Fluid Dynamics: Theory, Computation, and Numerical Simulation Second Edition
Fluid Dynamics: Theory, Computation, and Numerical Simulation Second Edition C. Pozrikidis m Springer Contents Preface v 1 Introduction to Kinematics 1 1.1 Fluids and solids 1 1.2 Fluid parcels and flow
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
THE VORTEX PANEL METHOD
THE VORTEX PANEL METHOD y j m α V 4 3 2 panel 1 a) Approimate the contour of the airfoil by an inscribed polygon with m sides, called panels. Number the panels clockwise with panel #1 starting on the lower
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
Chapter 3 Bernoulli Equation
1 Bernoulli Equation 3.1 Flow Patterns: Streamlines, Pathlines, Streaklines 1) A streamline, is a line that is everywhere tangent to the velocity vector at a given instant. Examples of streamlines around
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
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
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
UNSTEADY LOW REYNOLDS NUMBER FLOW PAST TWO ROTATING CIRCULAR CYLINDERS BY A VORTEX METHOD
Proceedings of the 3rd ASME/JSME Joint Fluids Engineering Conference Jul 8-23, 999, San Francisco, California FEDSM99-8 UNSTEADY LOW REYNOLDS NUMBER FLOW PAST TWO ROTATING CIRCULAR CYLINDERS BY A VORTEX
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
6.1 Momentum Equation for Frictionless Flow: Euler s Equation The equations of motion for frictionless flow, called Euler s
Chapter 6 INCOMPRESSIBLE INVISCID FLOW All real fluids possess viscosity. However in many flow cases it is reasonable to neglect the effects of viscosity. It is useful to investigate the dynamics of an
Apply mass and momentum conservation to a differential control volume. Simple classical solutions of NS equations
Module 5: Navier-Stokes Equations: Appl mass and momentum conservation to a differential control volume Derive the Navier-Stokes equations Simple classical solutions of NS equations Use dimensional analsis
MAE 101A. Homework 7 - Solutions 3/12/2018
MAE 101A Homework 7 - Solutions 3/12/2018 Munson 6.31: The stream function for a two-dimensional, nonviscous, incompressible flow field is given by the expression ψ = 2(x y) where the stream function has
Calculation of Potential Flow Around An Elliptic Cylinder Using Boundary Element Method
Calculation of Potential Flow Around An Elliptic Cylinder Using Boundary Element Method M. Mushtaq Saima Nazir N. A. Shah, Ph.D. G. Muhammad Abstract In this paper, a direct boundary element method is
Continuum Mechanics Lecture 7 Theory of 2D potential flows
Continuum Mechanics ecture 7 Theory of 2D potential flows Prof. http://www.itp.uzh.ch/~teyssier Outline - velocity potential and stream function - complex potential - elementary solutions - flow past a
Offshore Hydromechanics
Offshore Hydromechanics Module 1 : Hydrostatics Constant Flows Surface Waves OE4620 Offshore Hydromechanics Ir. W.E. de Vries Offshore Engineering Today First hour: Schedule for remainder of hydromechanics
Fluid Dynamics Problems M.Sc Mathematics-Second Semester Dr. Dinesh Khattar-K.M.College
Fluid Dynamics Problems M.Sc Mathematics-Second Semester Dr. Dinesh Khattar-K.M.College 1. (Example, p.74, Chorlton) At the point in an incompressible fluid having spherical polar coordinates,,, the velocity
HW6. 1. Book problems 8.5, 8.6, 8.9, 8.23, 8.31
HW6 1. Book problems 8.5, 8.6, 8.9, 8.3, 8.31. Add an equal strength sink and a source separated by a small distance, dx, and take the limit of dx approaching zero to obtain the following equations for
Fundamentals of Fluid Mechanics
Sixth Edition Fundamentals of Fluid Mechanics International Student Version BRUCE R. MUNSON DONALD F. YOUNG Department of Aerospace Engineering and Engineering Mechanics THEODORE H. OKIISHI Department
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
The Bernoulli Equation
The Bernoulli Equation The most used and the most abused equation in fluid mechanics. Newton s Second Law: F = ma In general, most real flows are 3-D, unsteady (x, y, z, t; r,θ, z, t; etc) Let consider
Pressure in stationary and moving fluid Lab- Lab On- On Chip: Lecture 2
Pressure in stationary and moving fluid Lab-On-Chip: Lecture Lecture plan what is pressure e and how it s distributed in static fluid water pressure in engineering problems buoyancy y and archimedes law;
The Divergence Theorem Stokes Theorem Applications of Vector Calculus. Calculus. Vector Calculus (III)
Calculus Vector Calculus (III) Outline 1 The Divergence Theorem 2 Stokes Theorem 3 Applications of Vector Calculus The Divergence Theorem (I) Recall that at the end of section 12.5, we had rewritten Green
TME225 Learning outcomes 2018: week 1
J. TME225 Learning outcomes 2018 360 J TME225 Learning outcomes 2018 Note that the questions related to the movies are not part of the learning outcomes. They are included to enhance you learning and understanding.
u = (u, v) = y The velocity field described by ψ automatically satisfies the incompressibility condition, and it should be noted that
18.354J Nonlinear Dynamics II: Continuum Systems Lecture 1 9 Spring 2015 19 Stream functions and conformal maps There is a useful device for thinking about two dimensional flows, called the stream function
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
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
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
The purpose of this lecture is to present a few applications of conformal mappings in problems which arise in physics and engineering.
Lecture 16 Applications of Conformal Mapping MATH-GA 451.001 Complex Variables The purpose of this lecture is to present a few applications of conformal mappings in problems which arise in physics and
V (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
FLUID DYNAMICS, THEORY AND COMPUTATION MTHA5002Y
UNIVERSITY OF EAST ANGLIA School of Mathematics Main Series UG Examination 2017 18 FLUID DYNAMICS, THEORY AND COMPUTATION MTHA5002Y Time allowed: 3 Hours Attempt QUESTIONS 1 and 2, and THREE other questions.
Rate of Flow Quantity of fluid passing through any section (area) per unit time
Kinematics of Fluid Flow Kinematics is the science which deals with study of motion of liquids without considering the forces causing the motion. Rate of Flow Quantity of fluid passing through any section
called the potential flow, and function φ is called the velocity potential.
J. Szantr Lectre No. 3 Potential flows 1 If the flid flow is irrotational, i.e. everwhere or almost everwhere in the field of flow there is rot 0 it means that there eists a scalar fnction ϕ,, z), sch
FLUID MECHANICS. Chapter 3 Elementary Fluid Dynamics - The Bernoulli Equation
FLUID MECHANICS Chapter 3 Elementary Fluid Dynamics - The Bernoulli Equation CHAP 3. ELEMENTARY FLUID DYNAMICS - THE BERNOULLI EQUATION CONTENTS 3. Newton s Second Law 3. F = ma along a Streamline 3.3
APPH 4200 Physics of Fluids
APPH 4200 Physics of Fluids Review (Ch. 3) & Fluid Equations of Motion (Ch. 4) September 21, 2010 1.! Chapter 3 (more notes) 2.! Vorticity and Circulation 3.! Navier-Stokes Equation 1 Summary: Cauchy-Stokes
Chapter 2 Dynamics of Perfect Fluids
hapter 2 Dynamics of Perfect Fluids As discussed in the previous chapter, the viscosity of fluids induces tangential stresses in relatively moving fluids. A familiar example is water being poured into
3.25 Pressure form of Bernoulli Equation
CEE 3310 Control Volume Analysis, Oct 3, 2012 83 3.24 Review The Energy Equation Q Ẇshaft = d dt CV ) (û + v2 2 + gz ρ d + (û + v2 CS 2 + gz + ) ρ( v n) da ρ where Q is the heat energy transfer rate, Ẇ
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
CHAPTER 3 Introduction to Fluids in Motion
CHAPTER 3 Introduction to Fluids in Motion FE-tpe Eam Review Problems: Problems 3- to 3-9 nˆ 0 ( n ˆi+ n ˆj) (3ˆi 4 ˆj) 0 or 3n 4n 0 3. (D) 3. (C) 3.3 (D) 3.4 (C) 3.5 (B) 3.6 (C) Also n n n + since ˆn
Aerodynamics of Spinning Sphere in Ideal Flow R. C. Mehta Department of Aeronautical Engineering, Noorul Islam University, Kumaracoil , India
Scholars Journal of Engineering and Technology (SJET) Sch. J. Eng. Tech., 06; 4(5):5-9 Scholars Academic and Scientific Publisher (An International Publisher for Academic and Scientific Resources) www.saspublisher.com
Matlab GUI for Elementary Flows as an Educational Tool
Matlab GUI for Elementary Flows as an Educational Tool Gabriel A. Heredia Acevedo, Bernardo Restrepo, and Jonathan Holguino Polytechnic University of Puerto Rico Abstract Elementary flows in fluid mechanics
!! +! 2!! +!"!! =!! +! 2!! +!"!! +!!"!"!"
Homework 4 Solutions 1. (15 points) Bernoulli s equation can be adapted for use in evaluating unsteady flow conditions, such as those encountered during start- up processes. For example, consider the large
CEE 3310 Control Volume Analysis, Oct. 7, D Steady State Head Form of the Energy Equation P. P 2g + z h f + h p h s.
CEE 3310 Control Volume Analysis, Oct. 7, 2015 81 3.21 Review 1-D Steady State Head Form of the Energy Equation ( ) ( ) 2g + z = 2g + z h f + h p h s out where h f is the friction head loss (which combines
Vorticity Equation Marine Hydrodynamics Lecture 9. Return to viscous incompressible flow. N-S equation: v. Now: v = v + = 0 incompressible
13.01 Marine Hydrodynamics, Fall 004 Lecture 9 Copyright c 004 MIT - Department of Ocean Engineering, All rights reserved. Vorticity Equation 13.01 - Marine Hydrodynamics Lecture 9 Return to viscous incompressible
1.060 Engineering Mechanics II Spring Problem Set 3
1.060 Engineering Mechanics II Spring 2006 Due on Monday, March 6th Problem Set 3 Important note: Please start a new sheet of paper for each problem in the problem set. Write the names of the group members
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)
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
Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 2012/13
Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 212/13 Exam 2ª época, 2 February 213 Name : Time : 8: Number: Duration : 3 hours 1 st Part : No textbooks/notes allowed 2 nd Part :
Unit C-1: List of Subjects
Unit C-: List of Subjects The elocity Field The Acceleration Field The Material or Substantial Derivative Steady Flow and Streamlines Fluid Particle in a Flow Field F=ma along a Streamline Bernoulli s
3.5 Vorticity Equation
.0 - Marine Hydrodynamics, Spring 005 Lecture 9.0 - Marine Hydrodynamics Lecture 9 Lecture 9 is structured as follows: In paragraph 3.5 we return to the full Navier-Stokes equations (unsteady, viscous
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
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
Aerodynamics. Lecture 1: Introduction - Equations of Motion G. Dimitriadis
Aerodynamics Lecture 1: Introduction - Equations of Motion G. Dimitriadis Definition Aerodynamics is the science that analyses the flow of air around solid bodies The basis of aerodynamics is fluid dynamics
7 EQUATIONS OF MOTION FOR AN INVISCID FLUID
7 EQUATIONS OF MOTION FOR AN INISCID FLUID iscosity is a measure of the thickness of a fluid, and its resistance to shearing motions. Honey is difficult to stir because of its high viscosity, whereas water
AERODYNAMICS STUDY NOTES UNIT I REVIEW OF BASIC FLUID MECHANICS. Continuity, Momentum and Energy Equations. Applications of Bernouli s theorem
AERODYNAMICS STUDY NOTES UNIT I REVIEW OF BASIC FLUID MECHANICS. Continuity, Momentum and Energy Equations. Applications of Bernouli s theorem UNIT II TWO DIMENSIONAL FLOWS Complex Potential, Point Source
APPLIED FLUID DYNAMICS HANDBOOK
APPLIED FLUID DYNAMICS HANDBOOK ROBERT D. BLEVINS H imhnisdia ttodisdiule Darmstadt Fachbereich Mechanik 'rw.-nr.. [VNR1 VAN NOSTRAND REINHOLD COMPANY ' ' New York Contents Preface / v 1. Definitions /
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
Egon Krause. Fluid Mechanics
Egon Krause Fluid Mechanics Egon Krause Fluid Mechanics With Problems and Solutions, and an Aerodynamic Laboratory With 607 Figures Prof. Dr. Egon Krause RWTH Aachen Aerodynamisches Institut Wüllnerstr.5-7
Figure 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)
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
Homework Two. Abstract: Liu. Solutions for Homework Problems Two: (50 points total). Collected by Junyu
Homework Two Abstract: Liu. Solutions for Homework Problems Two: (50 points total). Collected by Junyu Contents 1 BT Problem 13.15 (8 points) (by Nick Hunter-Jones) 1 2 BT Problem 14.2 (12 points: 3+3+3+3)
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
Continuum Mechanics Lecture 5 Ideal fluids
Continuum Mechanics Lecture 5 Ideal fluids Prof. http://www.itp.uzh.ch/~teyssier Outline - Helmholtz decomposition - Divergence and curl theorem - Kelvin s circulation theorem - The vorticity equation
Investigation potential flow about swept back wing using panel method
INTERNATIONAL JOURNAL OF ENERGY AND ENVIRONMENT Volume 7, Issue 4, 2016 pp.317-326 Journal homepage: www.ijee.ieefoundation.org Investigation potential flow about swept back wing using panel method Wakkas
Fluids. Fluid = Gas or Liquid. Density Pressure in a Fluid Buoyancy and Archimedes Principle Fluids in Motion
Chapter 14 Fluids Fluids Density Pressure in a Fluid Buoyancy and Archimedes Principle Fluids in Motion Fluid = Gas or Liquid MFMcGraw-PHY45 Chap_14Ha-Fluids-Revised 10/13/01 Densities MFMcGraw-PHY45 Chap_14Ha-Fluids-Revised
Fluid 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
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
Lift Enhancement on Unconventional Airfoils
Lift Enhancement on nconventional Airfoils W.W.H. Yeung School of Mechanical and Aerospace Engineering Nanang Technological niversit, North Spine (N3), Level 2 50 Nanang Avenue, Singapore 639798 mwheung@ntu.edu.sg
CLASS SCHEDULE 2013 FALL
CLASS SCHEDULE 2013 FALL Class # or Lab # 1 Date Aug 26 2 28 Important Concepts (Section # in Text Reading, Lecture note) Examples/Lab Activities Definition fluid; continuum hypothesis; fluid properties
FLUID 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
Fluids. Fluids in Motion or Fluid Dynamics
Fluids Fluids in Motion or Fluid Dynamics Resources: Serway - Chapter 9: 9.7-9.8 Physics B Lesson 3: Fluid Flow Continuity Physics B Lesson 4: Bernoulli's Equation MIT - 8: Hydrostatics, Archimedes' Principle,
FLUID 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
Numerical Simulation of Unsteady Aerodynamic Coefficients for Wing Moving Near Ground
ISSN -6 International Journal of Advances in Computer Science and Technology (IJACST), Vol., No., Pages : -7 Special Issue of ICCEeT - Held during -5 November, Dubai Numerical Simulation of Unsteady Aerodynamic
CEE 3310 Control Volume Analysis, Oct. 10, = dt. sys
CEE 3310 Control Volume Analysis, Oct. 10, 2018 77 3.16 Review First Law of Thermodynamics ( ) de = dt Q Ẇ sys Sign convention: Work done by the surroundings on the system < 0, example, a pump! Work done
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