# 6.1 Momentum Equation for Frictionless Flow: Euler s Equation The equations of motion for frictionless flow, called Euler s

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1 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 ideal fluid that is incompressible and has zero viscosity. The analysis of ideal fluid motions is simpler than that for viscous flows because no shear stresses are present in inviscid flow. Normal stresses are the only presses that must be considered in the analysis. The normal stress in an inviscid flow is the negative of the thermodynamic pressure, σ nn =-p. 6.1 Momentum Equation for Frictionless Flow: Euler s Equation The equations of motion for frictionless flow, called Euler s

2 equations. (μ=0, σ xx =σ yy =σ zz =-p in Navier-Stokes equation) Vector Form: In cylindrical coordinates:

3 6.2 Euler s Equations in Streamline Coordinates In describing the motion of a fluid particle in a steady (unsteady) flow, the distance along a streamline is a logical coordinate to use in writing the equations of motion. For simplicity, consider the flow in the yz plane shown in Fig The equations of motion are to be written in terms of the coordinate s, distance along a streamline, and the coordinate n,

4 distance normal to the streamline. Apply Newton s 2 nd law in the streamwise (the s) direction: where β is the angle between the tangent to the streamline and the horizontal, and a s is the acceleration of the fluid particle along the streamline.

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6 For steady flow, and neglecting body forces:

7 Equation 6.5 b indicates that a decrease in velocity is accompanied by an increase in pressure and conversely. Apply Newton s 2 nd law in the n direction: where β is the angle between the n direction and the vertical, and a n is the acceleration of the fluid particle in the n direction. We obtain

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9 For steady flow in a horizontal plane: Equation 6.6b indicates that pressure increases in the direction outward from the center of curvature of the streamlines. In regions where the streamlines are straight, the radius of curvature, R, is infinite and there is no pressure variation normal to the streamlines. Ex. 6.1 Flow in a bend: Compute the approximate flow rate.

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11 6.3 Bernoulli Equation Integration of Euler s Equation along a streamline for Steady Flow Derivation Using Streamline Coordinates

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13 The Bernoulli equation is powerful and useful equation because it relates pressure changes to velocity and elevation changes along a streamline. However, it gives correct results only when applied to a flow situation whenever all four of the restrictions are reasonable. In general, the Bernoulli constant in Eq. 6.9 has different values along different streamlines. For the case of irrotational flow, the constant has a single value throughout the entire flow field Derivation Using Rectangular Coordinates

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16 As expected, we see that the last two equations are identical to Eqs. 6.8 and 6.9 derived previously using streamline coordinates.

17 The Bernoulli equation, derived using rectangular coordinates, is still subject to the restrictions: (1) steady flow, (2) incompressible flow, (3) frictionless flow, and (4) flow along a streamline Static, Stagnation, and Dynamic Pressures The pressure, p, which we have used in deriving the Bernoulli equation, E. 6.9, is the thermodynamic pressure; is commonly called the static pressure. The static pressure is that pressure which would be measured by an instrument moving with the flow. However, such a measurement is rather difficult to make in a practical situation! How do we measure static pressure experimentally? In Section 6-2 we showed that there was no pressure variation

18 normal to straight streamlines. This fact makes it possible to measure the static pressure in a flowing fluid using a wall pressure tap, placed in a region where the flow streamlines are straight, as shown in Fig. 6.2a. The pressure tap is a small hole, drilled carefully in the wall,

19 with its axis perpendicular to the surface. If the hole is perpendicular to the duct wall and free from burrs, accurate measurements of static pressure can be made by connecting the tap to a suitable pressure-measuring instrument. In a fluid stream far from a wall, or where streamlines are curved, accurate static pressure measurements can be made by careful use of a static pressure probe, shown in Fig. 6.2b. Such probes must be designed so that the measuring holes are placed correctly with respect to the probe tip and stem to avoid erroneous results. In use, the measuring section must be aligned with the local flow direction. Static pressure probes are available commercially in sizes as small as 1.5 mm (1/16 in.) in diameter. The stagnation pressure is obtained when a flowing fluid is

20 decelerated to zero speed by a frictionless process. In incompressible flow, the Bernoulli equation can be used to related changes in speed and pressure along a streamline for such a process. The term 1/2ρV 2 generally is called the dynamic pressure.

21 Thus, if the stagnation pressure and static pressure could be measured at a point, Eq would give the local flow speed. Stagnation pressure is measured in the laboratory using a probe with a hole that faces directly upstream as shown in Fig Such a probe is called a stagnation pressure probe, or pitot tube.

22 If we knew the stagnation pressure and static pressure at a same point, then the flow speed could be computed form Eq Two possible experimental setups are shown in Fig. 6.4 In Fig. 6.4a, the static pressure corresponding to point A is read from the wall static pressure tap. The stagnation pressure is

23 measured directly at A by the total head tube, as shown. (The stem of the total head tube is placed downstream from the measurement location to minimize disturbance of the local flow.) Two probes often are combined, as in the pitot-static tube

24 shown in Fig. 6.4b. The inner tube is used to measure the stagnation pressure at point B, while the static pressure at C is sensed using the small holes in the outer tube. In flow fields where the static pressure variation in the streamwise direction is small, the pito-static tube may be used to infer the speed at point B in the flow by assuming p B =p C and using Eq Remember tat the Bernoulli equation applies only for incompressible flow (Mach number, M 0.3). Ex. 6.2 Pitot Tube: Find the flow speed.

25 6.3.4 Applications where subscripts 1 and 2 represent any two points on a streamline.

26 Ex. 6.3 Nozzle Flow: Find p 1 -p atm.

27 Ex. 6.4 Flow through a Siphon: Find (a) Speed of water leaving as a free jet, (b) Pressure at point A in the flow. Ex. 6.5 Flow under a Sluice Gate: Find (a) V2, (b) Q/w (ft 3 /s per

28 foot of width) Ex. 6.6 Bernoulli Equation in Translating Reference Frame: Find, p B p 0 A

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30 6.3.5 Cautions on Use of the Bernoulli Equation Flow through nozzle was modeled well by the Bernoulli equation. Because the pressure gradient in a nozzle is favorable, there is no separation and boundary layers on the walls remain thin. Friction has a negligible effect on the low velocity profile, so 1-D flow is a good model. A diverging passage or sudden expansion should not be

31 modeled using the Bernoulli equation. Adverse pressure gradients cause rapid growth of boundary layers, severely distorted velocity profiles, and possible flow separation. 1-D flow is a poor model for such flows. The hydraulic jump is an example of an open-channel flow with adverse pressure gradient. Flow through a hydraulic jump is mixed violently, making it impossible to identify streamlines. Thus the Bernoulli equation cannot be used to model flow through a hydraulic jump. The Bernoulli equation cannot be applied through a machine such as propeller, pump, or windmill. It is impossible to have locally steady flow or to identify streamlines during flow through a machine. Temperature changes can cause significant changes in density

32 of a gas, even for low-speed flow. Thus the Bernoulli equation could not be applied to air flow through a heating element (e.g., of a hand-held hair dryer) where temperature changes are significant. 6.4 Relation Between The 1 st Law of Thermodynamics and the Bernoulli Equation The Bernoulli equation, Eq. 6.9, was obtained by integrating Euler s equation along a streamline for steady, incompressible, frictionless flow. Thus Eq. 6.9 was derived from the momentum equation for a fluid particle. An equation identical in form to Eq. 6.9 (although requiring very different restrictions) may be obtained from the 1 st law of thermodynamics.

33 Consider steady flow in the absence of shear forces. We choose a control volume bounded by streamlines along is periphery. Such a boundary, shown in Fig. 6.5, often is called a stream tube.

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37 Equation 6.16 is identical in form to the Bernoulli equation, Eq The Bernoulli equation was derived from momentum

38 considerations (Newton s 2 nd law), and is valid for steady, incompressible, frictionless flow along a streamline. Equation 6.16 was obtained by applying the 1 st law of thermodynamics to a stream tube control volume, subject to restrictions 1 through 7 above. Thus the Bernoulli equation (Eq. 6.9) and the identical form of the energy equation (Eq. 6.16) were developed from entirely different models, coming from entirely different basic concepts, and involving different restrictions. Note that the restriction 7 (u 2 -u 1 -δq/dm=0) was necessary to obtain the Bernoulli equation form the 1 st law of thermodynamics. This restriction can be satisfied if δq/dm is zero (there is no heat transfer to the fluid) and u 2 =u 1 (there is no change in the

39 internal thermal energy of the fluid). The restriction also is satisfied if (u 2- u 1 ) and δq/dm are nonzero provided that the two terms are equal (this is true for incompressible frictionless flow). For the special case considered in this section it is true that the 1 st law of thermodynamics reduces to the Bernoulli equation. The Bernoulli equation was obtained by integrating the differential form of Newton s 2 nd law (Euler s equation) for steady, incompressible, frictionless flow along a streamline. Each term in the Bernoulli equation has dimensions of energy per unit mass. The Bernoulli equation may be viewed as a mechanical energy balance. In those cases wherein there is no conversion of mechanical to thermal energy, mechanical energy and thermal

40 energy are separately conserved. For these cases, the 1 st law of thermodynamics and Newton s 2 nd law do not yield separate information. However, in general, the 1 st law of thermodynamics and Newton s 2 nd law are independent equations that must be satisfied separately. Ex. 6.7 Internal energy and heat transfer in frictionless incompressible flow: u 2 -u 1 =δq/dm Ex. 6.8 frictionless flow with heat transfer:

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42 For steady, frictionless, incompressible flow along a streamline, we have shown that the 1 st law of thermodynamics reduces to the Bernoulli equation. From Eq we conclude that there is no loss of mechanical energy in such a flow. Often it is convenient to represent the mechanical energy level

43 of a flow graphically. The energy grade line (EGL) represents the total head height. Liquid would rise to the EGL height in a total head tube placed in the flow. The hydraulic grade line (HGL) height represents the sum of

44 the elevation and static pressure heads, z+p/ρg. In a static pressure tap attached to the flow conduit, liquid would rise to the HGL height. The difference in heights between the EGL and the HGL represents the dynamic (velocity) head, V 2 /2g.

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46 : the free surface in the large reservoir. There the velocity is negligible and the pressure is atmospheric. : The velocity head increases from zero to V 2 2 /2g as the liquid accelerates into the first section of constant-diameter tube. : The velocity increase again in the reducer between and. : The velocity become constant between and. : At the free discharge at section, the static head is zero. 6.5 Unsteady Bernoulli Equation- Integration of Euler s Equation Along a Streamline The momentum equation for frictionless flow was found to be

47 1 DV p gk ρ = Dt (6.3) It can be converted to a scalar equation by taking the dot product with ds, where ds is an element of distance along a streamline. Thus

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49 To evaluate the integral term in Eq. 6.21, the variation in V / t must be known as a function of s, the distance along the streamline measured from point 1. Ex. 6.9 Unsteady Bernoulli Equaiton

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51 6.6 Irrotational Flow An irrotational flow is one in which fluid elements moving in the flow field do not undergo any rotation. For ω = 0, V = 0

52 In cylindrical coordinates Bernoulli Equation Applied to Irrotational Flow If, in addition to being inviscid, steady, and incompressible, the flow field is also irrotational, we can show that Bernoulli s equation can be applied between any two points in the flow To illustrate this, we start with Euler s equation in vector form,

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54 Since dr was an arbitrary displacement, Eq is valid between any two points in a steady, incompressible, inviscid flow

55 that is also irrotational Velocity Potential In Section 5.2 we formulated the stream function, ψ, which relates the streamlines and mass flow rate in 2-D, incompressible flow. We can formulate a relation called the potential function, φ, for a velocity field tat is irrotational. To do so, we must use the fundamental vector identity which is valid if is a scalar function having continuous first and second derivatives. Then, for an irrotational flow in which V = 0, a scalar

56 function, φ, must exist such that the gradient of φ is proportional to the velocity vector, V. In order that the positive direction of flow be in the direction of decreasing φ, we define φ so that In cylindrical coordinates

57 The velocity potential, φ, exist only for irrotational flow. The stream function, ψ, satisfies the continuity equation for incompressible flow; the stream function is not subject to the restriction of irrotational flow. Irrotationality may be a valid assumption for those regions of a flow in which viscous forces are negligible, i.e. a region exists outside the boundary layer in the flow over a solid surface. The theory for irrotational flow is developed in terms of an imaginary ideal fluid whose viscosity is identically zero. Since,

58 in an irrotational flow, the velocity field may be defined by the potential function, φ, the theory is often referred to as potential flow theory. All real fluids possess viscosity, but there are many situations in which the assumption of inviscid flow considerably simplifies the analysis and, at the same time, gives meaningful results ψ and φ for 2-D, Irrotational, Incompressible Flow: Laplace Equation

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60 Equation 6.30 and 6.31 are forms of Laplace s equation- an equation that arises in many areas of the physical sciences and engineering. Any function φ and ψ that satisfies Laplace s equation represent a possible 2-D, incompressible, irrotational flow field.

61 Comparing Eqs and 6.33, we see that the slope of a

62 constant ψ line at any point is the negative reciprocal of the slope of the constant φ line at that point; lines of constant ψ and constant φ are orthogonal. This property of potential lines and streamlines is useful in graphical analyses of flow fields. Ex Velocity potential, ψ =ax 2 -ay 2, where a=3 s -1. Show that the flow is irrotational. Find: φ Elementary Plane Flows A variety of potential flows can be constructed by superposing elementary flow patterns. The φ and ψ functions for five elementary 2-D flows- a uniform flow( 均勻流 ), a source( 源 ), a sink( 沈 ), a vortex( 渦流 ),

63 and a doublet( 偶流 ). Uniform flow: inclined at angle α to the x axis, ψ=(u cosα)y-(u sinα)x, φ=-(u sinα)y-(u cosα)x Source: flow is radially outward from the z axis and symmetrical in all directions. Sink: flow is radially inward; a sink is a negative source. Sources and sinks have no exact physical counterparts. The primary value of the concept of sources and sinks is that, when combined with other elementary flows, they produce flow patterns that adequately represent realistic flows.

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65 Vortex: the velocity distribution in an irrotational vortex can 2 1 dp Vθ be determined from Euler s equation ( = ) and the ρ dr r Bernoulli equation ( dp = VdV θ θ ). ρ 2 Vθ dr = V θ dv θ Vdr θ + rdvθ = 0 rv θ = constant r Doublet: this flow is produced mathematically by allowing a source and a sink of numerically equal strengths to merge.

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67 6.6.5 Superposition of Elementary Plane Flows Both φ and ψ satisfy Laplace s equation for flow that is both incompressible and irrotational. Since Laplace s equation is a linear, homogeneous PDE, solution may be superposed to develop more complex and interesting patterns of flow. The object of superposition of elementary flow is to produce flow patterns similar to those of practical interest. Since there is no flow across a streamline, any streamline contour can be imagined to represent a solid surface. Through the end of the nineteenth century, workers in pure hydrodynamics failed to produce results that agreed with experiment. Potential flows produced body shapes with lift but predicted zero drag (the d Alembert paradox ). Two influences changed this situation: first Prandtl introduced

68 the BL concept and began to develop the theory, and the second, interest in aeronautics increased dramatically int the early 1900s. Prandtl showed by mathematical analysis and through elegantly simple experiments that viscous effects are confined to a thin boundary layer on the surface of a body. Even for real fluids, flow outside the BL behaves as though the fluid had zero viscosity. Pressure gradients from the external flow are impressed on the BL. The most important input to a calculation of the real fluid flow in the BL is the pressure distribution. Once the velocity field is known from the potential flow solution, the pressure distribution may be calculated. Two methods of combining elementary flows may be used. The direct method consists of combining elementary flows.

69 Distributed line sources, sinks, and images may be used to create bodies of arbitrary shape. (mathematical techniques: complex variables and conformal transformations, can be used to obtain flow fields for interesting geometries) The inverse methods of superposition calculates the body shape to produce a desired pressure distribution. (a large computer code must be used.)

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73 Ex Flow over a cylinder: superposition of doublet and uniform flow.

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79 Ex Flow over a cylinder: superposition of doublet, uniform flow, and clockwise free vortex.

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