Engineering Fluid Mechanics
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Fluid Mechanics
FLUID MECHANICS PROF. DR. METİN GÜNER COMPILER ANKARA UNIVERSITY FACULTY OF AGRICULTURE DEPARTMENT OF AGRICULTURAL MACHINERY AND TECHNOLOGIES ENGINEERING 1 1. INTRODUCTION Mechanics is the oldest physical science that deals with both stationary and moving bodies under the influence of forces. Mechanics is divided into three groups: a) Mechanics of rigid bodies, b) Mechanics of deformable bodies, c) Fluid mechanics Fluid mechanics deals with the behavior of fluids at rest (fluid statics) or in motion (fluid dynamics), and the interaction of fluids with solids or other fluids at the boundaries (Fig.1.1.). Fluid mechanics is the branch of physics which involves the study of fluids (liquids, gases, and plasmas) and the forces on them. Fluid mechanics can be divided into two. a)Fluid Statics b)Fluid Dynamics Fluid statics or hydrostatics is the branch of fluid mechanics that studies fluids at rest. It embraces the study of the conditions under which fluids are at rest in stable equilibrium Hydrostatics is fundamental to hydraulics, the engineering of equipment for storing, transporting and using fluids. Hydrostatics offers physical explanations for many phenomena of everyday life, such as why atmospheric pressure changes with altitude, why wood and oil float on water, and why the surface of water is always flat and horizontal whatever the shape of its container. Fluid dynamics is a subdiscipline of fluid mechanics that deals with fluid flow— the natural science of fluids (liquids and gases) in motion. It has several subdisciplines itself, including aerodynamics (the study of air and other gases in motion) and hydrodynamics (the study of liquids in motion). -
Fluid Mechanics
cen72367_fm.qxd 11/23/04 11:22 AM Page i FLUID MECHANICS FUNDAMENTALS AND APPLICATIONS cen72367_fm.qxd 11/23/04 11:22 AM Page ii McGRAW-HILL SERIES IN MECHANICAL ENGINEERING Alciatore and Histand: Introduction to Mechatronics and Measurement Systems Anderson: Computational Fluid Dynamics: The Basics with Applications Anderson: Fundamentals of Aerodynamics Anderson: Introduction to Flight Anderson: Modern Compressible Flow Barber: Intermediate Mechanics of Materials Beer/Johnston: Vector Mechanics for Engineers Beer/Johnston/DeWolf: Mechanics of Materials Borman and Ragland: Combustion Engineering Budynas: Advanced Strength and Applied Stress Analysis Çengel and Boles: Thermodynamics: An Engineering Approach Çengel and Cimbala: Fluid Mechanics: Fundamentals and Applications Çengel and Turner: Fundamentals of Thermal-Fluid Sciences Çengel: Heat Transfer: A Practical Approach Crespo da Silva: Intermediate Dynamics Dieter: Engineering Design: A Materials & Processing Approach Dieter: Mechanical Metallurgy Doebelin: Measurement Systems: Application & Design Dunn: Measurement & Data Analysis for Engineering & Science EDS, Inc.: I-DEAS Student Guide Hamrock/Jacobson/Schmid: Fundamentals of Machine Elements Henkel and Pense: Structure and Properties of Engineering Material Heywood: Internal Combustion Engine Fundamentals Holman: Experimental Methods for Engineers Holman: Heat Transfer Hsu: MEMS & Microsystems: Manufacture & Design Hutton: Fundamentals of Finite Element Analysis Kays/Crawford/Weigand: Convective Heat and Mass Transfer Kelly: Fundamentals -
Lecture 1: Introduction
Lecture 1: Introduction E. J. Hinch Non-Newtonian fluids occur commonly in our world. These fluids, such as toothpaste, saliva, oils, mud and lava, exhibit a number of behaviors that are different from Newtonian fluids and have a number of additional material properties. In general, these differences arise because the fluid has a microstructure that influences the flow. In section 2, we will present a collection of some of the interesting phenomena arising from flow nonlinearities, the inhibition of stretching, elastic effects and normal stresses. In section 3 we will discuss a variety of devices for measuring material properties, a process known as rheometry. 1 Fluid Mechanical Preliminaries The equations of motion for an incompressible fluid of unit density are (for details and derivation see any text on fluid mechanics, e.g. [1]) @u + (u · r) u = r · S + F (1) @t r · u = 0 (2) where u is the velocity, S is the total stress tensor and F are the body forces. It is customary to divide the total stress into an isotropic part and a deviatoric part as in S = −pI + σ (3) where tr σ = 0. These equations are closed only if we can relate the deviatoric stress to the velocity field (the pressure field satisfies the incompressibility condition). It is common to look for local models where the stress depends only on the local gradients of the flow: σ = σ (E) where E is the rate of strain tensor 1 E = ru + ruT ; (4) 2 the symmetric part of the the velocity gradient tensor. The trace-free requirement on σ and the physical requirement of symmetry σ = σT means that there are only 5 independent components of the deviatoric stress: 3 shear stresses (the off-diagonal elements) and 2 normal stress differences (the diagonal elements constrained to sum to 0). -
Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles ------Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles
UOT Mechanical Department / Aeronautical Branch Gas Dynamics Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles -------------------------------------------------------------------------------------------------------------------------------------------- Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles 16.1 Exit Flow for Underexpanded and Overexpanded Supersonic Nozzles The variation in flow patterns inside the nozzle obtained by changing the back pressure, with a constant reservoir pressure, was discussed early. It was shown that, over a certain range of back pressures, the flow was unable to adjust to the prescribed back pressure inside the nozzle, but rather adjusted externally in the form of compression waves or expansion waves. We can now discuss in detail the wave pattern occurring at the exit of an underexpanded or overexpanded nozzle. Consider first, flow at the exit plane of an underexpanded, two-dimensional nozzle (see Figure 16.1). Since the expansion inside the nozzle was insufficient to reach the back pressure, expansion fans form at the nozzle exit plane. As is shown in Figure (16.1), flow at the exit plane is assumed to be uniform and parallel, with . For this case, from symmetry, there can be no flow across the centerline of the jet. Thus the boundary conditions along the centerline are the same as those at a plane wall in nonviscous flow, and the normal velocity component must be equal to zero. The pressure is reduced to the prescribed value of back pressure in region 2 by the expansion fans. However, the flow in region 2 is turned away from the exhaust-jet centerline. To maintain the zero normal-velocity components along the centerline, the flow must be turned back toward the horizontal. -
Multidisciplinary Design Project Engineering Dictionary Version 0.0.2
Multidisciplinary Design Project Engineering Dictionary Version 0.0.2 February 15, 2006 . DRAFT Cambridge-MIT Institute Multidisciplinary Design Project This Dictionary/Glossary of Engineering terms has been compiled to compliment the work developed as part of the Multi-disciplinary Design Project (MDP), which is a programme to develop teaching material and kits to aid the running of mechtronics projects in Universities and Schools. The project is being carried out with support from the Cambridge-MIT Institute undergraduate teaching programe. For more information about the project please visit the MDP website at http://www-mdp.eng.cam.ac.uk or contact Dr. Peter Long Prof. Alex Slocum Cambridge University Engineering Department Massachusetts Institute of Technology Trumpington Street, 77 Massachusetts Ave. Cambridge. Cambridge MA 02139-4307 CB2 1PZ. USA e-mail: [email protected] e-mail: [email protected] tel: +44 (0) 1223 332779 tel: +1 617 253 0012 For information about the CMI initiative please see Cambridge-MIT Institute website :- http://www.cambridge-mit.org CMI CMI, University of Cambridge Massachusetts Institute of Technology 10 Miller’s Yard, 77 Massachusetts Ave. Mill Lane, Cambridge MA 02139-4307 Cambridge. CB2 1RQ. USA tel: +44 (0) 1223 327207 tel. +1 617 253 7732 fax: +44 (0) 1223 765891 fax. +1 617 258 8539 . DRAFT 2 CMI-MDP Programme 1 Introduction This dictionary/glossary has not been developed as a definative work but as a useful reference book for engi- neering students to search when looking for the meaning of a word/phrase. It has been compiled from a number of existing glossaries together with a number of local additions. -
Normal and Oblique Shocks, Prandtl Meyer Expansion
Aerothermodynamics of high speed flows AERO 0033{1 Lecture 3: Normal and oblique shocks, Prandtl Meyer expansion Thierry Magin, Greg Dimitriadis, and Adrien Crovato [email protected] Aeronautics and Aerospace Department von Karman Institute for Fluid Dynamics Aerospace and Mechanical Engineering Department Faculty of Applied Sciences, University of Li`ege Wednesday 9am { 12:15pm February { May 2021 1 / 36 Outline Normal shock Total and critical quantities Oblique shock Prandtl-Meyer expansion Shock reflection and shock interaction 2 / 36 Outline Normal shock Total and critical quantities Oblique shock Prandtl-Meyer expansion Shock reflection and shock interaction 2 / 36 Normal shock relations (inviscid flow) Rankine-Hugoniot relations for steady normal shock σ = 0; v = u ex ; n = ex ! σn(U2 − U1) = (F · n)2 − (F · n)1 ρ2u2 = ρ1u1 2 2 ρ2u2 + p2 = ρ1u1 + p1 ρ2u2H2 = ρ1u1H1 I Eqs. also valid for non calorically perfect gases I Contact discontinuity when u2 = u1 = 0 ! p2 = p1 I Otherwise, the total enthalpy conservation can be expressed as 2 2 2 u cp p γ p2 u2 γ p1 u1 H2 = H1 with H = h+ ; h = ! + = + 2 R ρ γ − 1 ρ2 2 γ − 1 ρ1 2 I Non-linear algebraic system of 3 eqs. in 3 unknowns ρ2, u2, and p2 with closed solution expressed in function of dimensionless parameters: Machp number M1 = u1=a1 and specific heat ratio γ, with a1 = γRT1 3 / 36 Normal shock relations for calorically perfect gases For M1 > 1 (derivation given further in this section) 2 ρ2 u1 (γ+1)M1 I ρ = u = 2 > 1 1 2 2+(γ−1)M1 p2 = 1 + 2γ (M2 − 1) > 1 I p1 γ+1 1 γ−1 2 2 1+ 2 -
Chapter 3 Newtonian Fluids
CM4650 Chapter 3 Newtonian Fluid 2/5/2018 Mechanics Chapter 3: Newtonian Fluids CM4650 Polymer Rheology Michigan Tech Navier-Stokes Equation v vv p 2 v g t 1 © Faith A. Morrison, Michigan Tech U. Chapter 3: Newtonian Fluid Mechanics TWO GOALS •Derive governing equations (mass and momentum balances •Solve governing equations for velocity and stress fields QUICK START V W x First, before we get deep into 2 v (x ) H derivation, let’s do a Navier-Stokes 1 2 x1 problem to get you started in the x3 mechanics of this type of problem solving. 2 © Faith A. Morrison, Michigan Tech U. 1 CM4650 Chapter 3 Newtonian Fluid 2/5/2018 Mechanics EXAMPLE: Drag flow between infinite parallel plates •Newtonian •steady state •incompressible fluid •very wide, long V •uniform pressure W x2 v1(x2) H x1 x3 3 EXAMPLE: Poiseuille flow between infinite parallel plates •Newtonian •steady state •Incompressible fluid •infinitely wide, long W x2 2H x1 x3 v (x ) x1=0 1 2 x1=L p=Po p=PL 4 2 CM4650 Chapter 3 Newtonian Fluid 2/5/2018 Mechanics Engineering Quantities of In more complex flows, we can use Interest general expressions that work in all cases. (any flow) volumetric ⋅ flow rate ∬ ⋅ | average 〈 〉 velocity ∬ Using the general formulas will Here, is the outwardly pointing unit normal help prevent errors. of ; it points in the direction “through” 5 © Faith A. Morrison, Michigan Tech U. The stress tensor was Total stress tensor, Π: invented to make the calculation of fluid stress easier. Π ≡ b (any flow, small surface) dS nˆ Force on the S ⋅ Π surface V (using the stress convention of Understanding Rheology) Here, is the outwardly pointing unit normal of ; it points in the direction “through” 6 © Faith A. -
Introduction
CHAPTER 1 Introduction "For some years I have been afflicted with the belief that flight is possible to man." Wilbur Wright, May 13, 1900 1.1 ATMOSPHERIC FLIGHT MECHANICS Atmospheric flight mechanics is a broad heading that encompasses three major disciplines; namely, performance, flight dynamics, and aeroelasticity. In the past each of these subjects was treated independently of the others. However, because of the structural flexibility of modern airplanes, the interplay among the disciplines no longer can be ignored. For example, if the flight loads cause significant structural deformation of the aircraft, one can expect changes in the airplane's aerodynamic and stability characteristics that will influence its performance and dynamic behavior. Airplane performance deals with the determination of performance character- istics such as range, endurance, rate of climb, and takeoff and landing distance as well as flight path optimization. To evaluate these performance characteristics, one normally treats the airplane as a point mass acted on by gravity, lift, drag, and thrust. The accuracy of the performance calculations depends on how accurately the lift, drag, and thrust can be determined. Flight dynamics is concerned with the motion of an airplane due to internally or externally generated disturbances. We particularly are interested in the vehicle's stability and control capabilities. To describe adequately the rigid-body motion of an airplane one needs to consider the complete equations of motion with six degrees of freedom. Again, this will require accurate estimates of the aerodynamic forces and moments acting on the airplane. The final subject included under the heading of atmospheric flight mechanics is aeroelasticity. -
Nozzle Aerodynamics Baseline Design
Preliminary Design Review Supersonic Air-Breathing Redesigned Engine Nozzle Customer: Air Force Research Lab Advisor: Brian Argrow Team Members: Corrina Briggs, Jared Cuteri, Tucker Emmett, Alexander Muller, Jack Oblack, Andrew Quinn, Andrew Sanchez, Grant Vincent, Nathaniel Voth Project Description Model, manufacture, and verify an integrated nozzle capable of accelerating subsonic exhaust to supersonic exhaust produced from a P90-RXi JetCat engine for increased thrust and efficiency from its stock configuration. Stock Nozzle Vs. Supersonic Nozzle Inlet Compressor Combustor Turbine Project Baseline Nozzle Nozzle Test Nozzle Project Description Design Aerodynamics Bed Integration Summary Objectives/Requirements •FR 1: The Nozzle Shall accelerate the flow from subsonic to supersonic conditions. •FR 2: The Nozzle shall not decrease the Thrust-to-Weight Ratio. •FR 3: The Nozzle shall be designed and manufactured such that it will integrate with the JetCat Engine. •DR 3.1: The Nozzle shall be manufactured using additive manufacturing. •DR 3.4: Successful integration of the nozzle shall be reversible such that the engine is operable in its stock configuration after the new nozzle has been attached, tested, and detached. •FR4: The Nozzle shall be able to withstand engine operation for at least 30 seconds. Project Baseline Nozzle Nozzle Test Nozzle Project Description Design Aerodynamics Bed Integration Summary Concept of Operations JetCat P90-SE Subsonic Supersonic Engine Flow Flow 1. Remove Stock Nozzle 2. Additive Manufactured 3-D Nozzle -
Chapter 15 - Fluid Mechanics Thursday, March 24Th
Chapter 15 - Fluid Mechanics Thursday, March 24th •Fluids – Static properties • Density and pressure • Hydrostatic equilibrium • Archimedes principle and buoyancy •Fluid Motion • The continuity equation • Bernoulli’s effect •Demonstration, iClicker and example problems Reading: pages 243 to 255 in text book (Chapter 15) Definitions: Density Pressure, ρ , is defined as force per unit area: Mass M ρ = = [Units – kg.m-3] Volume V Definition of mass – 1 kg is the mass of 1 liter (10-3 m3) of pure water. Therefore, density of water given by: Mass 1 kg 3 −3 ρH O = = 3 3 = 10 kg ⋅m 2 Volume 10− m Definitions: Pressure (p ) Pressure, p, is defined as force per unit area: Force F p = = [Units – N.m-2, or Pascal (Pa)] Area A Atmospheric pressure (1 atm.) is equal to 101325 N.m-2. 1 pound per square inch (1 psi) is equal to: 1 psi = 6944 Pa = 0.068 atm 1atm = 14.7 psi Definitions: Pressure (p ) Pressure, p, is defined as force per unit area: Force F p = = [Units – N.m-2, or Pascal (Pa)] Area A Pressure in Fluids Pressure, " p, is defined as force per unit area: # Force F p = = [Units – N.m-2, or Pascal (Pa)] " A8" rea A + $ In the presence of gravity, pressure in a static+ 8" fluid increases with depth. " – This allows an upward pressure force " to balance the downward gravitational force. + " $ – This condition is hydrostatic equilibrium. – Incompressible fluids like liquids have constant density; for them, pressure as a function of depth h is p p gh = 0+ρ p0 = pressure at surface " + Pressure in Fluids Pressure, p, is defined as force per unit area: Force F p = = [Units – N.m-2, or Pascal (Pa)] Area A In the presence of gravity, pressure in a static fluid increases with depth. -
Equation of Motion for Viscous Fluids
1 2.25 Equation of Motion for Viscous Fluids Ain A. Sonin Department of Mechanical Engineering Massachusetts Institute of Technology Cambridge, Massachusetts 02139 2001 (8th edition) Contents 1. Surface Stress …………………………………………………………. 2 2. The Stress Tensor ……………………………………………………… 3 3. Symmetry of the Stress Tensor …………………………………………8 4. Equation of Motion in terms of the Stress Tensor ………………………11 5. Stress Tensor for Newtonian Fluids …………………………………… 13 The shear stresses and ordinary viscosity …………………………. 14 The normal stresses ……………………………………………….. 15 General form of the stress tensor; the second viscosity …………… 20 6. The Navier-Stokes Equation …………………………………………… 25 7. Boundary Conditions ………………………………………………….. 26 Appendix A: Viscous Flow Equations in Cylindrical Coordinates ………… 28 ã Ain A. Sonin 2001 2 1 Surface Stress So far we have been dealing with quantities like density and velocity, which at a given instant have specific values at every point in the fluid or other continuously distributed material. The density (rv ,t) is a scalar field in the sense that it has a scalar value at every point, while the velocity v (rv ,t) is a vector field, since it has a direction as well as a magnitude at every point. Fig. 1: A surface element at a point in a continuum. The surface stress is a more complicated type of quantity. The reason for this is that one cannot talk of the stress at a point without first defining the particular surface through v that point on which the stress acts. A small fluid surface element centered at the point r is defined by its area A (the prefix indicates an infinitesimal quantity) and by its outward v v unit normal vector n . -
Gas Dynamics and Jet Propulsion
A Course Material on GAS DYNAMICS AND JET PROPULSION By Mr. C.RAVINDIRAN. ASSISTANT PROFESSOR DEPARTMENT OF MECHANICAL ENGINEERING SASURIE COLLEGE OF ENGINEERING VIJAYAMANGALAM – 638 056 QUALITY CERTIFICATE This is to certify that the e-course material Subject Code : ME2351 Subject : GAS DYNAMICS AND JET PROPULSION Class : III Year MECHANICAL ENGINEERING being prepared by me and it meets the knowledge requirement of the university curriculum. Signature of the Author Name : C. Ravindiran Designation: Assistant Professor This is to certify that the course material being prepared by Mr. C. Ravindiran is of adequate quality. He has referred more than five books amount them minimum one is from abroad author. Signature of HD Name: Mr. E.R.Sivakumar SEAL CONTENTS S.NO TOPIC PAGE NO UNIT-1 BASIC CONCEPTS AND ISENTROPIC 1.1 Concept of Gas Dynamics 1 1.1.1 Significance with Applications 1 1.2 Compressible Flows 1 1.2.1 Compressible vs. Incompressible Flow 2 1.2.2 Compressibility 2 1.2.3. Compressibility and Incompressibility 3 1.3 Steady Flow Energy Equation 5 1.4 Momentum Principle for a Control Volume 5 1.5 Stagnation Enthalpy 5 1.6 Stagnation Temperature 7 1.7 Stagnation Pressure 8 1.8 Stagnation velocity of sound 9 1.9 Various regions of flow 9 1.10 Flow Regime Classification 11 1.11 Reference Velocities 12 1.11.1 Maximum velocity of fluid 12 1.11.2 Critical velocity of sound 13 1.12 Mach number 16 1.13 Mach Cone 16 1.14 Reference Mach number 16 1.15 Crocco number 19 1.16 Isothermal Flow 19 1.17 Law of conservation of momentum 19 1.17.1 Assumptions