# AA200 Chapter 9 - Viscous flow along a wall

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1 AA200 Chapter 9 - Viscous flow along a wall

2 9.1 The no-slip condition 9.2 The equations of motion 9.3 Plane, Compressible Couette Flow (Review) 9.4 The viscous boundary layer on a wall 9.5 The laminar incompressible boundary layer 9.6 Compressible laminar boundary layers 9.7 Mapping a compressible to an incompressible boundary layer 9.8 Turbulent boundary layers 9.9 Falkner-Skan boundary layers 9.10 Transformation between flat plate and curved wall boundary layers 9.11 The Von Karman integral momentum equation 9.12 Thwaites method for integrating the Von Karman equation, discussion of M. Head s method for turbulent boundary layers 9.13 Problems

3 9.1 The no-slip condition Mean free path in a gas. Slip velocity. At ordinary temperatures and pressures the mean free path is very small.

4 9.2 The equations of motion Steady 2-D flow.

5 9.3 Plane, Compressible Couette Flow The upper wall moves at a velocity U while the lower wall is at rest. The temperature of the upper wall is T. The flow is assumed to be steady and extends to plus and minus infinity in the x-direction. Therefore the velocity and temperature only depend on y.

6

7 The equations of motion reduce to Both the pressure and shearing stress are uniform throughout the flow. The shearing stress is related to the velocity through the Newtonian constitutive relation. Where is the shear stress at the lower wall. The energy equation can be integrated with respect to the velocity. Energy integral

8 In terms of the friction coefficient and Reynolds number the wall friction coefficient for an adiabatic wall is determined in terms of the Prandtl, Reynolds and Mach numbers. Q w = 0 The Reynolds number can be expressed as

9 9.4 The viscous boundary layer on a wall Reference: Boundary Layer Theory by Schlichting The figure depicts the flow at low Reynolds number less than 100 or so.

10 As the Reynolds number is increased to several hundred or more the velocity profile near the wall becomes quite thin and the guiding effect of the plate leads to a situation where the vertical velocity is small compared to the horizontal velocity.

11 First consider the y - momentum equation. Using the approximations just discussed this equation reduces to. Integrate from the wall to the edge of the boundary layer. Substitute for the pressure in the x - momentum equation.

12 The energy equation simplifies to

13 Neglect the normal stress terms. where

14 Newtonian stress. Fourier's law. The laminar boundary layer equations.

15 Measures of boundary layer thickness. Displacement thickness Momentum thickness

16 9.6 The laminar incompressible boundary layer The equations of motion reduce to Boundary conditions The pressure

17 Introduce the stream function U = ψ y V = ψ x The continuity equation is identically satisfied and the momentum equation becomes: ψ y ψ xy ψ x ψ yy = U e du e dx + νψ yyy Boundary conditions ψ ( x,0) = 0 ψ y ( x,0) = 0 ψ y ( x, ) = U e

18 The zero pressure gradient, incompressible boundary layer. ψ y ψ xy ψ x ψ yy = νψ yyy Similarity variables ψ = ( 2νU x) 1/2 F( α ) α = y U 2νx 1/2 Velocity components Reynolds number is based on distance from the leading edge

19 Vorticity Derivatives Substitute into the stream function equation and simplify

20 The Blasius equation Boundary conditions

21 Friction coefficient C f = 2 R ex F αα 0 ( ) Normal velocity at the edge of the layer Boundary layer thickness Boundary layer shape factor H = δ * θ =

22 Let The Blasius equation can be expressed as Let Then Vorticity at the edge of the layer decays exponentially with distance from the wall. This support the approach where we divide the flow into separate regions of rotational and irrotational flow.

23

24 Numerical solution

25 The Blasius equation is invariant under a dilation group and this group can be used to generate the solution in one step! F α α [ 0] = e 3b ( 0.2) F α α [ 0] =

26 Another perspective: the dilational symmetry of the problem ψ y ψ xy ψ x ψ yy = νψ yyy ψ ( x,0) = 0 ψ y ( x,0) = 0 ψ y ( x, ) = U e Transform the governing equation x = e a x y = eb y ψ = e c ψ ψ y ψ x y ψ x ψ y y ν ψ y y y = e 2c a 2b ψ y ψ xy e 2c a 2b ψ x ψ yy νe c 3b ψ yyy = 0 The equation is invariant if and only if x = e a x y = e b y ψ = e a b ψ

27 Transform boundary curves and boundary functions At the wall ψ ( x,0 ) = 0 all x e a b ψ e a x,0 ψ y ( ) = 0 ψ x,0 ( ) = 0 all x ( x,0 ) = 0 all x e a 2b ψ ( y e a x,0) = 0 ψ y ( x,0) = 0 all x At y ψ y ( x, ) = U all x ea 2b ψ ( y e a x, ) = U all x The freestream boundary condition is invariant if and only if a = 2b

28 The governing equations and boundary conditions are invariant under the group: x = e 2b x y = eb y ψ = e b ψ The infinitesimal transformation. Expand near b = 0 ξ = 2x ζ = y η = ψ Characteristic equations Invariants α = dx 2x = dy y = dψ ψ y x F = ψ x We can expect the solution to be of the form Since the governing equations and boundary conditions are invariant under the group we can expect that the solution will also be invariant under the group. ψ = xf( α )

29 9.7 Falkner-Skan laminar boundary layers Free stream velocity. Substitute.

30 Apply a three-parameter dilation group to the equation. For invariance we require the parameters to be related as follows Boundary functions and boundary curves must also be invariant.

31 Free stream boundary condition. For invariance The group that leaves the problem as a whole invariant is The solution should be invariant under the same group

32 In summary Allow for a virtual origin in x Dimensionless similarity variables

33 The Falkner-Skan equation. H = δ * θ

34 Homework 4

35 9.5 The von Karman integral equation Integrate the boundary layer equations with respect to y Shape factor

36 9.8 Thwaites' method for approximate calculation of boundary layer parameters. From the momentum equation From the von Karman equation Nondimensionalize using θ and U e Define Thwaites argued that there should exist a universal function relating m and l(m).

37 Thwaites suggests using L( m) = m

38 Thwaites functions can be calculated explicitly for the Falkner-Skan boundary layers

39 N. Curle adjusted Thwaites' functions slightly especially near separation. L(m) Several researchers of the era suggest using which is consistent with the friction coefficient for the Blasius case

40 The von Karman equation becomes which integrates to

41

42 Example - surface velocity from the potential flow about a circular cylinder. Thwaites' method gives a finite momentum thickness at the forward stagnation point. This is useful in a wing leading edge calculation.

43 The parameter m.

44 9.9 Compressible laminar boundary layers The boundary layer admits an energy integral very similar to the one for Couette flow. Let. Substitute into the energy equation. Use the momentum equation to simplify and introduce the Prandtl number

45 Adiabatic wall, Prandtl number equals one. Stagnation temperature is constant through the boundary layer. Non-adiabatic wall, zero pressure gradient, Prandtl number equals one.

46 9.10 Mapping a compressible to an incompressible boundary layer Flow at the edge of the compressible boundary layer is isentropic.

47 Assume viscosity is linearly proportional to temperature Viscosity of the virtual flow is the viscosity of the gas evaluated at the stagnation temperature of the gas. Continuity and momentum equations T S - Sutherland reference temperature, 110K for Air. Transformation of coordinates between the real and virtual flow

48 Partial derivatives =?? Introduce the stream function for steady compressible flow. Let Real and virtual stream functions have the same value.

49 Partial derivatives of the stream function from the chain rule. Velocities Partial derivatives of U from the chain rule.

50 Convective terms of the momentum equation Cancel terms

52 At the edge of the boundary layer Now

53 Note that Where we have used

54 Viscous term. Note

55 The boundary layer momentum equation becomes

56 Drop the common multiplying factors

57 Now the momentum equation is expressed entirely in tildaed variables. =0

58 For an adiabatic wall, and a Prandtl number of one the factor in brackets is one and the equation maps exactly to the incompressible form. with boundary conditions Skin friction

59

60 In order to solve for the physical velocity profiles we need to determine the temperature in the boundary layer. Look at the case The energy equation was integrated earlier Use and We need to relate wall normal coordinates in the real and virtual flow

61 The spatial similarity variable in the virtual flow is

62 Spatial similarity variables in the two flows are related by The thickness of the compressible layer increases with Mach number.

63 Now

64 9.11 Turbulent boundary layers Impirical relations for the thickness of the incompressible case, useful over a limited range of Reynolds number. Or for a wider range of Reynolds number

65

66 Stanford University Department of Aeronautics and Astronautics

67

68 The incompressible wall friction coefficient

69 An impirical form of the velocity profile; the so-called 1/7th power law The problem with this profile is that it fails to capture one of the most important features of the turbulent boundary layer profile which is that the actual shape of the profile depends on Reynolds number. A much better, though still impirical, relation is the law of the wake developed by Don Coles at Caltech coupled with the universal law of the wall. In this approach the velocity profile is normalized by the wall friction velocity. Define dimensionless wall variables Reference: D. Coles, The Law of the Wake in the Turbulent Boundary Layer, J. Fluid Mech. Vol 1, 1956

70 The thickness of the boundary layer in wall units is and Once the Reynolds number is known most of the important properties of the boundary layer are known.

71 Velocity profile Viscous sublayer - wall to A Buffer layer - A to B Logarithmic and outer layer - B to C to D C = 5.1 κ = 0.4

72 Measurements of velocity in the logarithmic layer can be used to infer the skin friction from the law of the wall. C increase with increasing roughness Reynolds number k s R es = k s u* ν < 3 R es = k s u* ν > 100 Roughness height Hydraulically smooth Fully rough

73 Separating turbulent boundary layer

74 The method of M. Head 1960 applied to incompressible turbulent boundary layers U e ( x) δ At any position x the area flow in the boundary layer is Q = This can be arranged to read Q = δ 0 U dy δ δ δ U dy = U e dy 0 U e 1 U 0 U e dy = U e δ δ * 0 Entrainment velocity V e = d ( dx U e ( δ δ * )) ( ) Reference: M.R. Head, Entrainment in the Turbulent Boundary Layer, Aero. Res. Council. R&M 3152, 1960 x

75 Head defined the boundary layer shape factor ( ) H 1 = δ δ * His model consists of two assumptions: θ 1) Assume V e U e = 1 U e d dx U e δ δ * ( ) ( ) ( ) = F H 1 2) Assume H 1 = G( H ) H = δ * θ In addition he assumed that the skin friction followed the impirical formula due to Ludweig and Tillman C f = H R θ R θ = U eθ ν

76 H 1 = We will use F( H 1 ) = ( H 1 3.0) G H ( ) = ( H 1.1)

77 Several classical references recommend different functions for F and G Calculation of Separation Points in Incompressible Turbulent Flows T. CEBECI, G. J. MOSINSKIS, AND A. M. O. SMITH Douglas Aircraft Company, Long Beach, Calif. J. AIRCRAFT VOL. 9, NO. 9 Also Boundary Layer Theory H. Schlichting Recommend Schlichting uses is missing

78 Cebeci - Schlichting H G Gap dg dh Discontinuity H G G( H ) = I prefer a single smooth function ( H 1.1) dg dg dh dh = H 1.1 ( ) H H

79 Comparison

81 Typical range of H vs R ex for turbulent boundary layers

82 Recall the von Karman integral momentum equation For given initial conditions on theta and H and known free stream velocity distribution U e (x) this equation is solved along with the auxiliary equations C f = H R θ R θ = U eθ ν 1 U e d ( dx U eθh 1 ) = F( H 1 ) = ( H 1 3.0) H 1 = G( H ) = ( H 1.1)

83 Zero pressure gradient turbulent boundary layer C p = 0 R θ R θinitial = 0.664( R x min ) 1/2 R x min = 10,000 H H ( R x min ) = / = 2.59 R ex R ex Ln( C ) f C f = R ex 1/5 Ludweig-Tillman Blasius Ln( R ex )

84 Potential flow about a circular cylinder Thwaites' method gives a finite momentum thickness at the forward stagnation point. This is useful in a wing leading edge calculation.

85 R θ R θinitial = /2 12 R cylinder R ex min = 10,000 H H ( R x min ) = / = 2.59 R cylinder = U R ν = 105 φseparation = 151 R ex R ex C f Ln( C ) f R ex Ln( R ex )

86 R θ R θinitial = /2 12 R cylinder R ex min = 10,000 R cylinder = U R ν = 107 H H ( R x min ) = / = 2.59 φ separation = 166 R ex R ex C f Ln( C f ) R ex Ln( R ex )

87 9.12 Transformation between flat plate and curved wall boundary layers Boundary layer equations

88 Transform variables by adding an arbitrary function of x to the y coordinate ρ U U x + ρ V U y + P e x τ x y y = ρu U x dg U dx y + ρ V + U dg dx U y + P e x τ xy y = ρu U x U + ρv y + P e x τ xy y

89 Insert the transformations of variables and derivatives into the equations of motion. The result is that the equations are mapped to themselves.

90

91 Viscous-inciscid interaction algorithm in Figure 9.29

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