# Drag Reduction in Turbulent Boundary Layers with Half Wave Wall Oscillations

Authors: Maneesh Mishra; Martin Skote
Journal: Mathematical Problems in Engineering
 (2015)

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## Abstract

Spatial square waves with positive cycle are used as steady forcing technique to study drag reduction effects on a turbulent boundary layer flow. Pseudospectral method is used for performing direct numerical simulations on very high resolution grids. A smooth step function is employed to prevent Gibbs phenomenon at the sharp discontinuities of a square wave. The idea behind keeping only the positive cycle of the spatial forcing is to reduce the power consumption to boost net power savings. For some spatial frequency of the oscillations with half waves, it is possible to prevent recovery of skin friction back to the reference case values. A set of wall oscillation parameters is numerically simulated to study its effect on the power  budget.


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## Body

## 1. Introduction

Turbulent drag reduction is one of the active areas of research in fluid mechanics especially due to its global impact on sustainability challenges we are facing today. One of the active techniques for reducing drag is through spanwise oscillation of the wall which reduces the skin friction and promises to have large potential for energy savings.This curious phenomenon was first observed by Jung et al. [1] through direct numerical simulations (DNS) in a channel flow. Since then, a lot of research efforts have been made in this direction for different flow configurations like channel flow [2–9], pipe flow [10, 11], and boundary layer flows [12–14]. These investigations have been made either through experiments or using DNS.Most of these studies have dealt with temporal form of wall oscillations which are specified as(1)wty=0=Wmsinωt,where Wm is the amplitude and ω is the frequency of the imposed oscillations.A few studies have been devoted to explore the spatial oscillations and its impact on reducing skin friction has been found to be greater than for temporal oscillations [15–19]. Spatial oscillations can be realized by enforcing the following boundary condition: (2)wxy=0=Wmsinkx,where k is the spatial frequency of oscillation and is related to the wavelength (λ) as k=2π/λ.Spatial wall oscillation technique has its advantages and disadvantages. It can have greater drag reduction as compared to temporal oscillations and, hence, there are higher net energy savings. It is an open-loop method so we do not require an array of distributed sensors on the surface. However, the implementation remains a challenge as it requires numerous moving parts which makes it impractical. Although there have been advances in the field of material science research to realize such waveforms in practical situations, the physical realization still remains elusive with the current technology.Almost all of the previous works have implemented oscillation waveforms using sinusoidal functions. A recent study by Cimarelli et al. [20] explored different temporal waveforms. In this work, we would like to explore the possibility of using spatial square waves for drag reduction. In order to reduce the power required to incorporate these oscillations, we consider only the positive cycles of these oscillations. One of the ways to realize spatial oscillations can be via pulsed jets in the spanwise direction for the near wall region. Another possibility is to actively manipulate wall roughness optimally distributed along the surface. The main contribution of the present work is to illustrate the use of smooth step functions to approximate the square waves which otherwise may give rise to Gibbs phenomenon when using spectral methods.


## 2. Methodology

### 2.1. Governing Equations

The governing equations which are used for the simulations here are the Navier-Stokes equations which are formulated in terms of velocity-vorticity and written in tensor notation as(3)∂ui∂t=-∂p∂xi+ϵijkujωk-∂∂xi12ujuj+1Re∇2ui+Fi,(4)∂ui∂xi=0,where ui are the velocity components, ωi are the vorticity components, p denotes pressure, and Fi is the body force. The nondimensional constant Re=U∞δ∗/ν is the Reynolds number with U∞ being the streamwise freestream velocity, δ∗ is the displacement thickness at x=0, and ν is the kinematic viscosity. xi represents the coordinate system with (x,y,z) as streamwise, wall-normal, and spanwise coordinates and t denotes time.These equations are solved using a pseudospectral method with appropriate boundary conditions. The basic idea with spectral methods is to express the solution as a sum ofbasis functions and then compute their coefficients such that they satisfy the governing partial differential equations and the boundary conditions.A third-order Runge-Kutta-scheme is used to perform time integration for the nonlinear terms. A second-order Crank-Nicolson method is used for the linear terms. For removing aliasing errors, a 3/2-rule is applied to the evaluation of the nonlinear terms when calculating Fourier transforms in the wall parallel(x-z) plane. The numerical code (SIMSON [21]) used for the simulations in this work has been developed at KTH, Stockholm. Earlier simulations of both temporal [12, 13] and spatial [15, 16] wall forcing have been performed with the code.


### 2.2. Numerical Setup

Since we are trying to simulate a turbulent boundary layer with a spatially growing boundary layer, we need to choose our basis functions accordingly. A basic sketch for the computational setup is shown in Figure1. For the discretization in the streamwise-spanwise plane, Fourier basis is chosen assuming the solutions are periodic in these directions. However, for the wall normal direction, periodicity does not apply and Chebyshev polynomials are instead used as basis functions for the y (wall-normal) direction. The technique is similar to other spectral codes used for channel flows [5–8, 17, 18], and the spectral accuracy is a considerable advantage as compared to other discretizations, such as the finite volume methods used in, for example, [9, 14].Figure 1
Computational box as seen from the negativez-direction with the growth of boundary layer illustrated. Fringe region forces the solution back to the prescribed laminar inflow thus enforcing periodic boundary condition. The lower part illustrates the spanwise velocity forcing which is applied in a part of the wall under the turbulent boundary layer. Half square waves are used in the present study as shown in the bottom figure.For initializing the simulations, a laminar base flow is required and is given as the Blasius similarity solution [22]. A trip forcing using a random volume force is then incorporated at x=5 for the flow to undergo transition and thereafter we have turbulent flow regime. Figure 1 depicts this scheme.Particular attention must be given to the streamwise direction since the boundary layer is growing downstream and hence no natural periodicity exists in that direction. Therefore, for the purpose of artificially creating a periodic computational domain, a fringe region is introduced at the end to achieve this. The purpose of this fringe region is to dampen the velocity fluctuations to zero and bring the velocity field back to the laminar Blasius solution such that there are minimum upstream effects [23]. This is achieved by introducing the volume forcing Fi in (3):(5)Fi=λxu~i-ui,where λ(x) is the strength of the forcing and u~i is the laminar inflow velocity profile. The function λ is defined as(6)λx=λmaxfxwith(7)fx=Sx-xstartΔxrise-Sx-xendΔxfall+1.Here λmax is the maximum strength of the fringe, xstart and xend denote the spatial extent of the region where the fringe is nonzero, and Δxrise and Δxfall are the rise and fall distance of the fringe function, respectively. Figure 2 shows a schematic of how the fringe function varies. S(η) is a continuous step function that varies from zero for η≤0 to unity for η≥1 and is given by(8)Sη=0,η≤0,11+e1/η-1+1/η,0<η<1,1,η≥1.Figure 2
Schematic picture of the fringe region.


### 2.3. Wall Oscillation Implementation

The form of wall oscillation implemented here is a spatial square wave with only positive forcing to reduce power consumption. However, there are numerical challenges in implementing this using pseudospectral method. A square wave when represented using Fourier basis gives rise to Gibbs phenomenon which is shown in Figure3(a). When we try to approximate the strong discontinuity in the square wave, it results in strong oscillations at the edges. These result in spurious values causing numerical instability and large computational errors. Increasing the number of terms in the Fourier series approximation does reduce the oscillation but it does not eliminate it completely.Figure 3
Function approximations using finite Fourier series terms.
(a)
Square wave with Gibbs phenomenon
(b)
Smooth step functionIn order to avoid Gibbs phenomenon, we utilize the same step function as we used for fringe region (8). Using the step function is advantageous as it has continuous derivatives at all points and does not exhibit the spurious ringing phenomenon. Figure 3(b) shows the use of f(x) in implementing the wall boundary condition for the present simulations. By including only a few Fourier coefficients, we can approximate the function quite accurately and eliminate Gibbs rings.Spatial wall oscillation can be incorporated with the following boundary condition:(9)wxy=0=Wmfx,where f(x) is the same profile function as used for fringe region (see equation (7)) and Wm is the amplitude of the spatial oscillations.


### 2.4. Numerical Parameters

All quantities are nondimensionalized by the free-stream velocity (U∞) and the displacement thickness (δ∗) at the starting position of the simulation (x=0), where the flow is laminar. The Reynolds number is set by specifying Reδ∗=U∞δ∗/ν at the laminar inlet (x=0). Note that, unless otherwise stated, the + superscript indicates that the quantity is made nondimensional with the friction velocity of the unmanipulated boundary layer (the reference case), denoted by uτ0, and the kinematic viscosity (ν).A computational domain withLx=600, Ly=30, and Lz=34 is chosen with a mesh resolution of 800×201×144, respectively. The resolution of these simulations in wall units is Δx+=16, Δymin+=0.04, and Δz+=5.1. All scalings are done based on uτ0 from reference case at the starting position of wall forcing (x=200). Wall oscillation boundary conditions are employed between xstart=200 and xend=450 once it is ascertained that the flow has become fully turbulent. The Reynolds number based on momentum thickness varies between 450<ReΘ<715 in the control region.Table1 summarizes the parameters chosen for the steady spatial oscillation in the present work. Only the positive forcing has been employed for these simulation setups as shown in Figure 3(b). The spatial frequencies have been doubled and halved with respect to PS2 to see its impact on drag reduction performance. Also, the amplitude of oscillations is varied to understand its impact on drag reduction. The aim is to observe the effect of removing the negative forcing of the wall boundary and its effects on power budget and net energy savings. Figure 4 shows the wall boundary condition for the three parameter sets at Wm=0.5.Table 1
Oscillation parameters for the simulations presented.
Parameter set (PS)
W
m
k
PS1
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.0628
PS2
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.1256
PS3
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.2512Figure 4
Wall boundary condition set for spanwise velocity component for PS1, PS2, and PS3 atWm=0.5.


## 2.1. Governing Equations

The governing equations which are used for the simulations here are the Navier-Stokes equations which are formulated in terms of velocity-vorticity and written in tensor notation as(3)∂ui∂t=-∂p∂xi+ϵijkujωk-∂∂xi12ujuj+1Re∇2ui+Fi,(4)∂ui∂xi=0,where ui are the velocity components, ωi are the vorticity components, p denotes pressure, and Fi is the body force. The nondimensional constant Re=U∞δ∗/ν is the Reynolds number with U∞ being the streamwise freestream velocity, δ∗ is the displacement thickness at x=0, and ν is the kinematic viscosity. xi represents the coordinate system with (x,y,z) as streamwise, wall-normal, and spanwise coordinates and t denotes time.These equations are solved using a pseudospectral method with appropriate boundary conditions. The basic idea with spectral methods is to express the solution as a sum ofbasis functions and then compute their coefficients such that they satisfy the governing partial differential equations and the boundary conditions.A third-order Runge-Kutta-scheme is used to perform time integration for the nonlinear terms. A second-order Crank-Nicolson method is used for the linear terms. For removing aliasing errors, a 3/2-rule is applied to the evaluation of the nonlinear terms when calculating Fourier transforms in the wall parallel(x-z) plane. The numerical code (SIMSON [21]) used for the simulations in this work has been developed at KTH, Stockholm. Earlier simulations of both temporal [12, 13] and spatial [15, 16] wall forcing have been performed with the code.


## 2.2. Numerical Setup

Since we are trying to simulate a turbulent boundary layer with a spatially growing boundary layer, we need to choose our basis functions accordingly. A basic sketch for the computational setup is shown in Figure1. For the discretization in the streamwise-spanwise plane, Fourier basis is chosen assuming the solutions are periodic in these directions. However, for the wall normal direction, periodicity does not apply and Chebyshev polynomials are instead used as basis functions for the y (wall-normal) direction. The technique is similar to other spectral codes used for channel flows [5–8, 17, 18], and the spectral accuracy is a considerable advantage as compared to other discretizations, such as the finite volume methods used in, for example, [9, 14].Figure 1
Computational box as seen from the negativez-direction with the growth of boundary layer illustrated. Fringe region forces the solution back to the prescribed laminar inflow thus enforcing periodic boundary condition. The lower part illustrates the spanwise velocity forcing which is applied in a part of the wall under the turbulent boundary layer. Half square waves are used in the present study as shown in the bottom figure.For initializing the simulations, a laminar base flow is required and is given as the Blasius similarity solution [22]. A trip forcing using a random volume force is then incorporated at x=5 for the flow to undergo transition and thereafter we have turbulent flow regime. Figure 1 depicts this scheme.Particular attention must be given to the streamwise direction since the boundary layer is growing downstream and hence no natural periodicity exists in that direction. Therefore, for the purpose of artificially creating a periodic computational domain, a fringe region is introduced at the end to achieve this. The purpose of this fringe region is to dampen the velocity fluctuations to zero and bring the velocity field back to the laminar Blasius solution such that there are minimum upstream effects [23]. This is achieved by introducing the volume forcing Fi in (3):(5)Fi=λxu~i-ui,where λ(x) is the strength of the forcing and u~i is the laminar inflow velocity profile. The function λ is defined as(6)λx=λmaxfxwith(7)fx=Sx-xstartΔxrise-Sx-xendΔxfall+1.Here λmax is the maximum strength of the fringe, xstart and xend denote the spatial extent of the region where the fringe is nonzero, and Δxrise and Δxfall are the rise and fall distance of the fringe function, respectively. Figure 2 shows a schematic of how the fringe function varies. S(η) is a continuous step function that varies from zero for η≤0 to unity for η≥1 and is given by(8)Sη=0,η≤0,11+e1/η-1+1/η,0<η<1,1,η≥1.Figure 2
Schematic picture of the fringe region.


## 2.3. Wall Oscillation Implementation

The form of wall oscillation implemented here is a spatial square wave with only positive forcing to reduce power consumption. However, there are numerical challenges in implementing this using pseudospectral method. A square wave when represented using Fourier basis gives rise to Gibbs phenomenon which is shown in Figure3(a). When we try to approximate the strong discontinuity in the square wave, it results in strong oscillations at the edges. These result in spurious values causing numerical instability and large computational errors. Increasing the number of terms in the Fourier series approximation does reduce the oscillation but it does not eliminate it completely.Figure 3
Function approximations using finite Fourier series terms.
(a)
Square wave with Gibbs phenomenon
(b)
Smooth step functionIn order to avoid Gibbs phenomenon, we utilize the same step function as we used for fringe region (8). Using the step function is advantageous as it has continuous derivatives at all points and does not exhibit the spurious ringing phenomenon. Figure 3(b) shows the use of f(x) in implementing the wall boundary condition for the present simulations. By including only a few Fourier coefficients, we can approximate the function quite accurately and eliminate Gibbs rings.Spatial wall oscillation can be incorporated with the following boundary condition:(9)wxy=0=Wmfx,where f(x) is the same profile function as used for fringe region (see equation (7)) and Wm is the amplitude of the spatial oscillations.


## 2.4. Numerical Parameters

All quantities are nondimensionalized by the free-stream velocity (U∞) and the displacement thickness (δ∗) at the starting position of the simulation (x=0), where the flow is laminar. The Reynolds number is set by specifying Reδ∗=U∞δ∗/ν at the laminar inlet (x=0). Note that, unless otherwise stated, the + superscript indicates that the quantity is made nondimensional with the friction velocity of the unmanipulated boundary layer (the reference case), denoted by uτ0, and the kinematic viscosity (ν).A computational domain withLx=600, Ly=30, and Lz=34 is chosen with a mesh resolution of 800×201×144, respectively. The resolution of these simulations in wall units is Δx+=16, Δymin+=0.04, and Δz+=5.1. All scalings are done based on uτ0 from reference case at the starting position of wall forcing (x=200). Wall oscillation boundary conditions are employed between xstart=200 and xend=450 once it is ascertained that the flow has become fully turbulent. The Reynolds number based on momentum thickness varies between 450<ReΘ<715 in the control region.Table1 summarizes the parameters chosen for the steady spatial oscillation in the present work. Only the positive forcing has been employed for these simulation setups as shown in Figure 3(b). The spatial frequencies have been doubled and halved with respect to PS2 to see its impact on drag reduction performance. Also, the amplitude of oscillations is varied to understand its impact on drag reduction. The aim is to observe the effect of removing the negative forcing of the wall boundary and its effects on power budget and net energy savings. Figure 4 shows the wall boundary condition for the three parameter sets at Wm=0.5.Table 1
Oscillation parameters for the simulations presented.
Parameter set (PS)
W
m
k
PS1
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.0628
PS2
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.1256
PS3
(0.1, 0.25, 0.4, 0.5, 0.6, 0.75, 1)
0.2512Figure 4
Wall boundary condition set for spanwise velocity component for PS1, PS2, and PS3 atWm=0.5.


## 3. Results and Discussion

In this section, we look into two aspects of the results obtained from our numerical simulations. First, we look into attenuation ofcf values with respect to the reference case. Subsequently, we present the power budget based on the different forcings.


### 3.1. Skin Friction Attenuation

We compare skin friction from the unoscillated or the reference case with the oscillated cases. Skin friction coefficient for turbulent flows is defined as(10)cf=2uτU∞2,where uτ is the friction velocity and is computed based on mean streamwise velocity gradient at the wall:(11)uτ=ν∂u∂yy=0.The resulting drag reduction (DR) is then calculated from (12)DR%=100cf0-cfcf0,where cf0 is the skin friction of the reference case. In contrast to internal flows [1–11], the DR is varying in the downstream direction for the present case of boundary layer flow. Figure 5 shows the results for the skin friction variation along streamwise direction. All three cases show skin friction attenuation. As soon as wall oscillation is applied at xstart=200, we see a strong gradient which marks the spatial transient for cf. For PS1, we have a longer wavelength and, due to discontinuous half waves, we observe recovery of cf back towards the reference case. However, for PS2 and PS3, due to smaller wavelength, this recovery process is weaker. This is a crucial observation as it indicates that, with positive forcing itself, we can get drag reduction of a similar order of magnitude as with a full cycle of wall oscillation. This would reduce the power required for forcing the wall oscillation and this increases our net power saving as will be presented in the next section. At xend=450, the oscillations are stopped and skin friction attains the reference case values.Figure 5
Spatial development of skin friction along streamwise direction atWm=1.


### 3.2. Power Budget

To compute the net energy savings, we need to take into account the energy required for wall oscillation as compared to the savings due to drag reduction. The derivation of these terms was given for channel flow by Quadrio and Ricco [6] which was extended to the boundary layer case by Skote [13].In order to compute the saved powerPsav(%), DR (as percentage of ratio of skin-friction coefficients from reference and oscillated cases; see (12)) is integrated for the region with wall oscillation. The total saved power can be written as(13)Psav%=1L∫xstartxend‍DR%dx,where xstart denotes the position at which the wall oscillation is started, xend denotes the endpoint for oscillation, and L=xstart-xend.Similarly, the wall oscillation requires power input which can also be defined in terms of the friction power of the reference flow [13] and can be written as(14)Preq%=∫xstartxend‍ν∂w/∂yy=0Wdx∫xstartxend‍uτ02U∞dx.The net saved power is then defined asPnet=Psav-Preq. If Pnet is negative it indicates that the input power required to oscillate the wall is greater than the saved power due to streamwise drag reduction. However, it is possible that, for an optimized set of oscillation parameters, one may achieve positive energy budget. As reported by other researchers [15, 18, 19], a positive net energy is more attainable for spatial forcing than for temporal forcing.Power required for the three oscillation cases is shown in Figure6. For lower amplitudes of forcing, we require lesser power and it grows exponentially for larger amplitudes. For different spatial frequencies, there is not much difference in input power required. Figure 7 shows the power saved based on (13). Here, we see that with increasing amplitude, the power saving saturates after a limit. The effect of spatial frequency is rather interesting as we see that the power saved for PS2 and PS3 is almost the same. PS1 has a lower power saving and that can be attributed to the recovery to unoscillated skin friction values discussed previously in Section 3.1.Figure 6
Power required for wall oscillation.Figure 7
Power saved for the three chosen parameter sets.Figure8 shows the net power savings for the different parameter sets. PS2 with Wm=0.5 gives us the maximum net power saving (~18%) amidst our chosen parameter space. Performance quickly deteriorates for larger amplitudes which show negative net power savings indicating that we spend more power in oscillating the wall as compared to the power savings. No complete description of the drag reduction mechanism exists to date. Thus, the influence of the parameters on the drag reduction remains largely unexplained. The parameter space explored in the current work is definitely not exhaustive. Viotti et al. [17] show power budget statistics for a wide parameter space using sinusoidal wall oscillation. The maximum net power savings achieved is reported as 23% which was found at Wm+=6. On the other hand, they showed maximum net power savings of 6% at Wm+=12, which is the amplitude comparable to the present case. They concluded that lower amplitudes give higher net power savings, even though the drag reduction values are lower. The simulation cases in the present study are not as exhaustive due to the computational demands for spatially developing boundary layers. Nevertheless, for the current study we obtain the maximum savings of 18% at Wm+=10. The current suboptimal results may very well be further improved by increasing the parametric space.Figure 8
Net power savings for the three chosen parameter sets together with a quadratic curve fit.Although the results look promising in terms of the net power savings, one of the drawbacks of the proposed methodology is that it induces crossflow which might be undesirable in certain situations. In order to illustrate the phenomena, a horizontal plane aty+=10 is shown in Figure 9. The figure has been compressed by a factor 4 in the streamwise direction for better visualization. From the figure it is observed that, after the first oscillation stops, the streaks reorient themselves to the streamwise direction. However, a spanwise crossflow manifests itself as can be seen by the oblique streaks in the regions after the second and third periods of forcing.Figure 9
Half wave oscillations inducing crossflow in the spanwise direction. A horizontal plane (y+=10) in the computational box is shown. The dark grey indicates low-speed regions and lighter shades indicate high-speed patches. The plane is stretched by a factor of four in the spanwise direction for clarity.Note that this phenomena would not occur if a periodic function with equal amount of positive and negative spanwise wall velocity is used, as in the study of temporal nonsinusoidal wall forcing by Cimarelli et al. [20].


## 3.1. Skin Friction Attenuation

We compare skin friction from the unoscillated or the reference case with the oscillated cases. Skin friction coefficient for turbulent flows is defined as(10)cf=2uτU∞2,where uτ is the friction velocity and is computed based on mean streamwise velocity gradient at the wall:(11)uτ=ν∂u∂yy=0.The resulting drag reduction (DR) is then calculated from (12)DR%=100cf0-cfcf0,where cf0 is the skin friction of the reference case. In contrast to internal flows [1–11], the DR is varying in the downstream direction for the present case of boundary layer flow. Figure 5 shows the results for the skin friction variation along streamwise direction. All three cases show skin friction attenuation. As soon as wall oscillation is applied at xstart=200, we see a strong gradient which marks the spatial transient for cf. For PS1, we have a longer wavelength and, due to discontinuous half waves, we observe recovery of cf back towards the reference case. However, for PS2 and PS3, due to smaller wavelength, this recovery process is weaker. This is a crucial observation as it indicates that, with positive forcing itself, we can get drag reduction of a similar order of magnitude as with a full cycle of wall oscillation. This would reduce the power required for forcing the wall oscillation and this increases our net power saving as will be presented in the next section. At xend=450, the oscillations are stopped and skin friction attains the reference case values.Figure 5
Spatial development of skin friction along streamwise direction atWm=1.


## 3.2. Power Budget

To compute the net energy savings, we need to take into account the energy required for wall oscillation as compared to the savings due to drag reduction. The derivation of these terms was given for channel flow by Quadrio and Ricco [6] which was extended to the boundary layer case by Skote [13].In order to compute the saved powerPsav(%), DR (as percentage of ratio of skin-friction coefficients from reference and oscillated cases; see (12)) is integrated for the region with wall oscillation. The total saved power can be written as(13)Psav%=1L∫xstartxend‍DR%dx,where xstart denotes the position at which the wall oscillation is started, xend denotes the endpoint for oscillation, and L=xstart-xend.Similarly, the wall oscillation requires power input which can also be defined in terms of the friction power of the reference flow [13] and can be written as(14)Preq%=∫xstartxend‍ν∂w/∂yy=0Wdx∫xstartxend‍uτ02U∞dx.The net saved power is then defined asPnet=Psav-Preq. If Pnet is negative it indicates that the input power required to oscillate the wall is greater than the saved power due to streamwise drag reduction. However, it is possible that, for an optimized set of oscillation parameters, one may achieve positive energy budget. As reported by other researchers [15, 18, 19], a positive net energy is more attainable for spatial forcing than for temporal forcing.Power required for the three oscillation cases is shown in Figure6. For lower amplitudes of forcing, we require lesser power and it grows exponentially for larger amplitudes. For different spatial frequencies, there is not much difference in input power required. Figure 7 shows the power saved based on (13). Here, we see that with increasing amplitude, the power saving saturates after a limit. The effect of spatial frequency is rather interesting as we see that the power saved for PS2 and PS3 is almost the same. PS1 has a lower power saving and that can be attributed to the recovery to unoscillated skin friction values discussed previously in Section 3.1.Figure 6
Power required for wall oscillation.Figure 7
Power saved for the three chosen parameter sets.Figure8 shows the net power savings for the different parameter sets. PS2 with Wm=0.5 gives us the maximum net power saving (~18%) amidst our chosen parameter space. Performance quickly deteriorates for larger amplitudes which show negative net power savings indicating that we spend more power in oscillating the wall as compared to the power savings. No complete description of the drag reduction mechanism exists to date. Thus, the influence of the parameters on the drag reduction remains largely unexplained. The parameter space explored in the current work is definitely not exhaustive. Viotti et al. [17] show power budget statistics for a wide parameter space using sinusoidal wall oscillation. The maximum net power savings achieved is reported as 23% which was found at Wm+=6. On the other hand, they showed maximum net power savings of 6% at Wm+=12, which is the amplitude comparable to the present case. They concluded that lower amplitudes give higher net power savings, even though the drag reduction values are lower. The simulation cases in the present study are not as exhaustive due to the computational demands for spatially developing boundary layers. Nevertheless, for the current study we obtain the maximum savings of 18% at Wm+=10. The current suboptimal results may very well be further improved by increasing the parametric space.Figure 8
Net power savings for the three chosen parameter sets together with a quadratic curve fit.Although the results look promising in terms of the net power savings, one of the drawbacks of the proposed methodology is that it induces crossflow which might be undesirable in certain situations. In order to illustrate the phenomena, a horizontal plane aty+=10 is shown in Figure 9. The figure has been compressed by a factor 4 in the streamwise direction for better visualization. From the figure it is observed that, after the first oscillation stops, the streaks reorient themselves to the streamwise direction. However, a spanwise crossflow manifests itself as can be seen by the oblique streaks in the regions after the second and third periods of forcing.Figure 9
Half wave oscillations inducing crossflow in the spanwise direction. A horizontal plane (y+=10) in the computational box is shown. The dark grey indicates low-speed regions and lighter shades indicate high-speed patches. The plane is stretched by a factor of four in the spanwise direction for clarity.Note that this phenomena would not occur if a periodic function with equal amount of positive and negative spanwise wall velocity is used, as in the study of temporal nonsinusoidal wall forcing by Cimarelli et al. [20].


## 4. Conclusion

A new form of steady spatial wall oscillation technique in the form of square waves with positive forcing has been presented with promising results for developing an active drag reduction technique. Spectral methods were used to solve the governing equations and the use of a smooth step has been demonstrated to approximate a square wave to overcome Gibbs phenomenon and avoid sharp discontinuities. Downstream development of skin friction and power budget for different oscillation parameters have been presented. An optimal set of wall oscillation parameters for the current parameter space was found to have ~18% net energy savings.



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*Source: 253249-2015-06-24.xml*