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On the mesh resolution of industrial LES based on the DNS of flow over the T106C turbine
Advances in Aerodynamics volume 1, Article number: 21 (2019)
Abstract
A highorder NavierStokes solver based on the flux reconstruction (FR) or the correction procedure via reconstruction (CPR) formulation is employed to perform a direct numerical simulation (DNS) and large eddy simulations (LES) of a wellknown benchmark problem – transitional flow over the lowpressure T106C turbine cascade. Hprefinement studies are carried out to assess the resolution requirement. A 4th order (p3) simulation on the fine mesh is performed with a DNS resolution to establish a "converged" solution, including the mean pressure and skinfriction distributions, and the power spectral density in the wake. Then LES on the coarse and fine meshes with lower order schemes are conducted to assess the mesh and order dependence of the solution. In particular, we study the error in the transition location, the mean skinfriction distribution, and the mean lift and drag coefficients. These h and prefinement studies provide a muchneeded guideline in h and p resolutions to achieve a certain level of accuracy for industrial LES applications.
Introduction
Large eddy simulation [1] has received increased attention for industrial applications over the past decade for challenging vortexdominated turbulent flows [2–6]. Direct numerical simulations have also been used to study interesting flow physics at low Reynolds numbers, e.g. [7]. This is in part due to the advancements in computational algorithms and computing power of modern computers which paved the way for simulating more practical flow problems. In its 2030 vision [8], NASA has predicted that scale resolving simulations will be increasingly used for vortexdominated turbulent flow simulations such as rotorcraft flows and turbomachinery flows in aircraft engines.
The Reynolds Averaged NavierStokes (RANS) approach, which models all turbulent scales, has been widely used in industrial applications and its efficiency and accuracy were shown for nonseparated flows. However, the application of RANS to highly separated turbulent flow has not been very successful either because a statistically steady mean flow does not exist or the turbulence model is not adequate for such problems. In addition, RANS has serious limitations when it is used to tackle heat transfer and combustion problems [9, 10]. On the other hand, DNS, which resolves all turbulent scales, is prohibitively expensive even for problems at moderate Reynolds numbers. LES lies between RANS and DNS in terms of both accuracy and cost. Thus it opens a new avenue for tackling real world problems with superior accuracy and manageable cost.
In particular, turbomachinery flow is arguably one of the most challenging problems in computational fluid dynamics (CFD). These types of problems involve complex geometries and physics that requires high fidelity simulations and high accuracy [11]. Applications of LES and DNS simulation in turbomachinery problems have been conducted by many researchers [12–18]. Most previous computations have utilized finite difference (FD), compact difference (CD)[14, 19], and finitevolume (FV) [13, 20, 21] methods for the space discretization. While these methods possess desirable properties such as simplicity and ease of implementation, they suffer from either the lack of geometric flexibility in the case of (FD,CD) or larger stencils/less locality in the case of highorder (FV) schemes.
Therefore, a number of adaptive highorder methods capable of handling unstructured grids have been developed over the past few decades [22, 23]. These methods offer higher than 2nd order accuracy in space in addition to the compact/local nature of the required stencils. Thus, these methods are well suited for modern computing architectures such as GPUs or hybrid CPU/GPU due to their inherent elementlocal structure. In addition, they can handle different types of unstructured grids and hence can be applied to a wide range of industrial applications in contrast to classical FD/CD methods. Recently, a unifying framework called flux reconstruction [24] that encompasses several adaptive highorder methods was introduced by Huynh for hyperbolic conservation laws. This method was further extended to hybrid unstructured meshes [25, 26]. The class of adaptive highorder methods also includes the spectral difference method (SD) [27], spectral volume method (SV) [28], the discontinuous Galerkin method (DG) [29–31], and the hybrid DG/FV method [32].
In LES, there is the physical dissipation that is associated with the molecular viscosity. Numerical schemes introduce additional numerical dissipation in addition to the subgridscale (SGS) model dissipation. It has been shown that in some cases SGS models may be detrimental to the solution quality [33–36]. In practice, implicit LES (ILES) has proved its potential for turbulent flow simulations [4, 5, 37–39]. In the context of LES, highorder adaptive methods such as DG and FR/CPR have been shown to resolve a wider spectrum than the classical FD method, and are comparable to the CD method in terms of resolution power [40, 41].
In this paper, we employ an inhouse FR/CPR solver called hpMusic for the compressible NavierStokes equations to conduct DNS and LES simulations of a wellknown benchmark problem from one of the International Workshops on HighOrder CFD Methods [42], flow over the lowpressure turbine blade T106C cascade [43]. We focus on assessing the resolution required for a given error in the friction coefficient (Cf), the energy spectrum, and mean lift and drag coefficients. Some estimates are provided about the grid resolution, (streamwise, normal, spanwise) directions in wall units, to achieve a certain level of accuracy. We hope to help the turbomachinery community conduct faster and reliable LES to aid the design process.
The paper is organized as follows, Section 2 introduces the basic formulation of the FR/CPR method. We then describe the DNS of the T106C test case in Section 3. A study of LES resolution is presented in Section 4. Finally, conclusions are summarized in Section 5.
The FR/CPR method
The FR/CPR method introduced by Huynh [44] is a nodal numerical formulation for solving hyperbolic partial differential equations, which was extended to hybrid unstructured grids for conservation laws [25]. From the FR/CPR formulation, several interesting methods can be derived such as the SV, SD, and DG schemes among others [24, 25, 45–47]. In this large family of schemes, some schemes may provide larger time steps than the DG scheme [45]. Several groups have shown that the FR/CPR method is more efficient than the DG method [48]. For a complete review of the method, the reader can consult the following references [23, 49, 50].
In this section we present the FR/CPR method for a hyperbolic conservation law
with initial and boundary conditions, where the vector U consists of the conservative variables, and F is the flux. In the FR/CPR framework, the computational \(\mathcal {D}\) domain is discretized into a set of N_{e} nonoverlapping elements Ω_{i} such that \(\mathcal {D}\:=\: \cup _{i=1}^{N_{e}} \Omega _{i}\). By introducing an arbitrary test function W in each Ω_{i}, the weighted residual formulation of Eq. 1 on Ω_{i} can be expressed as
We approximate the conservative variables U_{i} inside each element by degree p polynomials using their nodal values at a set of points called solution points (SPs). After applying integration by parts to the divergence of flux, replacing the normal flux term with a common Riemann flux \(F^{n}_{com}\) and performing integration by parts again, we obtain
The common Reimann flux \(F^{n}_{com}\) is computed using a Riemann solver
where U_{i+} denotes the solution outside the current element, and n is the outward normal vector of the interface underconsideration. The normal flux at the interface is defined as
In order to eliminate the test function W, the face integral in Eq. 3 is transformed into an element integral. In order to achieve that, a "correction feild" δ_{i} is defined in each element as
where \(\left [\!\left [{F^{n}}\right ]\!\right ] = F^{n}_{com}  F^{n}(\mathbf {U}_{i}) \) is the normal flux jump. Combining Eqs. 3 and 6 we get
After some manipulations and by projecting the divergence of flux term onto the space of degree p polynomials [25], the final formulation for each solution point j is
where Π_{j} is the projection operator and subscript j denotes the jth solution point in the element.
Discretization of the viscous fluxes including the gradient of the conservative variables follows the second approach of Bassi and Rebay (BR2) [24, 46, 51]. After applying the space discretization, Eq. 8 reduces to a nonlinear ordinary differential equation (ODE) of the form
where R denotes the residual of the equation. The time marching is achieved using the implicit 2nd order backward difference formula (BDF2) coupled with a nonlinear block LUSGS (BLUSGS) [52, 53] solver.
DNS of transitional flow over the T106C blade
Case definition
The T106C case is selected as a challenging transitional flow problem for CFD simulations and has been widely used in assessing both numerical discretization accuracy and studying turbulent flow physics associated with such types of flows [12, 13, 16, 21, 54–56]. The configuration of the considered problem follows the setup introduced in the 4th International Workshop on HighOrder CFD Methods [42]. The blade has a chord of C=0.093 m, a pitch to chord ratio of 0.95, and a span to chord ratio of 10%. The inlet condition for the cascade is chosen such that the isentropic exit Mach number is M_{is}=0.65 and the Reynolds number is Re_{is}=80,000 based on the isentropic exit velocity. The inlet flow angle for this case is 32.7^{o}. This condition results in a transitional flow which is characterized by a long laminar separation bubble on the suction surface that transitions to turbulence further downstream leading to a fully turbulent wake.
The computational domain consists of six outer boundaries in addition to the blade wall, see Fig. 1. The imposed boundary conditions are periodic for the top and bottom boundaries and two spanwise boundaries, and characteristic inflow condition (specifying inlet total pressure and temperature and flow angle) for the inlet boundary, and characteristic outflow condition (imposing the outlet static pressure) at the outlet boundary. The wall boundary is specified as a noslip adiabatic boundary condition. The isentropic Mach number (M_{is}) on the blade surface is defined as
where P_{2s} is the pressure on the blade surface, and P_{∞} is the exit pressure.
H and prefinement studies
For the purpose of establishing a DNS solution, both grid (hrefinement) and order (prefinement) convergence studies were preformed. We use two meshes (coarse and fine) and polynomial orders up to p=4. The coarse mesh consists of 18,588 degree 2 hexahedral elements and the fine mesh is obtained from the coarse one by uniform refinement in each direction resulting in 148,704 elements Fig. 2. The coarse mesh is extruded from a 2D mesh with 6 layers in the spanwise direction. In order to have matching periodic edges at the top and bottom boundaries, we designed a sophisticated blockstructured mesh topology as shown in Fig. 1, which is generated using the PointWise mesh generation software. The mesh topology consists of an Otype block around the blade surface for resolution control in the boundary layer. Outside this Ogrid region a series of Htype blocks are used. The grid growth rate in the wall normal direction inside the Ogrid boundary layer block is 1.35. Outside the boundary layer region the mesh size grows gradually with a ratio that is less than 1.5 in most regions. It is worth noting that although the grid is of a blockstructured type, our numerical solver and scheme deal with it as an unstructured grid topology. The use of a blockstructured type was only to allow better control of the grid coarsening for the LES study in the streamwise, spanwise, and normal directions.
In this study we always start from a p0 steady solution and then restart to the p1 unsteady simulation and we continue to restart as the order increases. This is done after each simulation converges in time with respect to the mean flow quantities. We define the characteristic time as T_{c}=C/U_{∞}. The time averaging starts after the flow reaches a statistically steady state which based on our tests is about ≈108T_{c}. This was identified by monitoring the time histories of lift and drag, making sure it reaches that statistically steady state. It is hard for these types of flows to determine the correct transient region due to the highly unsteady nature. We note that not all the cases need this time to reach a statistically steady state but we are being more conservative here since some highorder simulations needed this long. The time used for averaging the flow quantities is 216T_{c}. This ensures the convergence of these mean quantities after performing a spanewise averaging as well. We also note that the time needed to converge the pressure distribution over the blade and hence the isentropic Mach number is much less than the time needed to converge the skinfriction.
The h and prefinement studies for the mean lift \(\overline {C_{L}}\) and drag \(\overline {C_{D}}\) coefficients are shown in Fig. 3. From this figure it can be clearly seen that the p3 (4^{th} order) solution on the fine mesh and p4 (5^{th} order) solution on the coarse mesh are nearly identical indicating the convergence of these quantities. In this paper, we study the mesh resolution in terms of the X_{+},Y_{+},Z_{+}, i.e., (streamwise, normal, spanwise) mesh resolutions in wall units. We define the equivalent \(\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}\) for highorder multidegree of freedom methods as
and the number of degrees of freedom (nDOF) per equation as
where N_{e} is the number of elements in the mesh, and d=3 is the dimension of the problem.
Table 1 shows the simulation data for all the cases including the averaged \(\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}\) on the blade wall, based on wall normal units. From this table we can see that the p3 solution on the fine mesh has the highest resolution in terms of averaged \(\left (\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+} \right)\) values. The distribution of \(\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}\) is also presented in Fig. 4 for the p3 on the fine mesh. It can be seen clearly from this figure that this p3 fine mesh resolution is a typical DNS resolution for such type of flow [12, 14].
Next, we consider the distribution of the pressure coefficient and the coefficient of streamwise skinfriction on the blade surface in Figs. 5 and 6. From these figures we can see that, similar to the mean \(\overline {C_{L}}\) and \(\overline {C_{D}}\) quantities, the p3 solution on the fine mesh is very close to the p4 solution on the coarse mesh. A closer look at these distribution is shown by zooming on the trailing edge in Fig. 5b for the pressure coefficient C_{p} and in Fig. 6b for the coefficient of streamwise friction C_{fs}. In particular, for the C_{fs} distribution we can see that the separation point is predicted correctly as in Hillewaert et al. [12] to be close to 0.7C_{axial}. The convergence in this transition region for the friction coefficient is much harder than the pressure coefficient, \(\overline {C_{L}}\) and \(\overline {C_{D}}\). This is due to the high intermittency of the separation and transition zones [12].
The power spectral density (PSD) of the pressure and the velocity magnitude is computed at two points in the wake. The first point is near the T.E. with coordinates (0.8591,−0.5137)C, while the second one is further in the wake downstream of the blade at location (0.9,−0.6)C. For these points we conduct a spanwise average using four locations in the spanwise direction, Z/C∈{0.0,0.025,0.05,0.075}. The Welch’s method of averaged periodograms [57] is utilized for the computation of the PSD. An efficient implementation of this method [58] is used in this paper. In this method the total time signal of the pressure is divided into subsets with 50% overlap between them and each subset is Hann windowed after the mean is subtracted. The definition of the PSD used in this work for any quantity of interest G is
where \(\hat {G}\) is the onesided amplitude as determined by performing a Fourier transform of the time signal, St=f C/U_{∞} is the Strouhal number based on the chord C and the exit velocity U_{∞}, and f is the frequency in Hz. Note that there is additional scaling applied to \(\hat {G}\) to account for multiplying by a window function [57]. The total time history used to compute the PSD is the same as the time needed for averaging the mean quantities of 216T_{c}. The windowed subsets are of length ≈35T_{c} each, resulting in a total of 11 subsets, and the data are collected with Δt=2.16×10^{−3}T_{c}. This results in a Strouhal number resolution of ΔSt≈0.03 and a cutoff St_{cutoff}≈231. In this work we have used the same spectral parameters for the computation of the PSD for all the cases.
Figure 7 presents the PSD of the pressure signal at wake point(2) after spanwise averaging the pressure at the four spanwise locations mentioned earlier. From this figure we can also see that all the cases were able to capture the positions of the peaks except the coarse mesh p1 results which missed the second peak, and the coarse mesh p2 which underestimated the PSD at the first peak. In addition, the pressure spectra in this figure follows the theoretical −7/3 slope based on the dimensional analysis of Kolmogorv’s theory for isotropic turbulence [59–61]. We note that this slope is not completely agreed on in the literature but can be seen in some cases [62] and has been reported by Marty et al. [13] for the flow around the T106C case. In Fig. 8, the PSD of the velocity magnitude also showed a good agreement with the theoretical slope of −5/3. However, for the velocity spectrum the point near the T.E. showed a better trend than the one further in the wake. This spectra PSD study shows the consistent convergence of the mesh and order resolutions up to the highest resolution of p3 on the fine mesh. Based on these results, we establish the p3 solution on the fine mesh as the DNS solution for the rest of the paper.
The comparison with experimental data of Michálek et al. [43] was rather difficult to obtain in the literature [12, 54, 55]. In Fig. 9, we present the comparison of the isentropic Mach number distribution on the blade surface with some of the results in the literature. From this figure it can be seen that on the pressure side we are able to show very good agreement with the experiment as in Hillewaert et al. [12]. However, on the suction side, there is a slight underprediction behavior up to the separation region and the suction peaks are overestimated. This observation is similar to most of the results in the literature and has been attributed to the difference in the inlet conditions between the experiment and the numerical simulations as conjectured by Hillewaert et al. [12]. We also note that Hillewaert et al. [12] has used a spanwise extent of 0.2C and Garai et al. [16] has used a 0.24C whereas our simulation only uses a 0.1C spanwise extent. In the experiment the spanwise extent was 2.4C. The reason for the shorter spans in the numerical simulations is to reduce the cost in addition to following the problem definition according to the highorder CFD workshop in our case. Moreover, in the previous numerical studies a grid or order dependence convergence was not systematically done to ensure reaching a DNS resolution. Nevertheless, we can see that our results are very close to Hillewaert et al. [12] who has reported having a \(\widetilde {Y}_{+} < 1.7 \) over the blade surface.
Finally, a qualitative comparison between the DNS solution and one of the LES simulations (p2 on the coarse mesh) is shown in Fig. 10. In this figure we present the isosurfaces of the qcriterion colored by the axial velocity. This figure shows the small structures that are captured by the DNS resolution in comparison to the larger structures that the LES was able to capture. In particular, the LES resolution captures the coherent structures and their breakdown near the separation bubble and the vortex shedding phenomena in the wake. However, in the DNS case those coherent structures are less spanwiseperiodic and straight than the LES case. The separation bubble extent is well captured by both resolutions as was evident for the distribution of C_{fs} Fig. 6b.
LES resolution study
In this section we study the effects of coarsening the mesh, in all directions, on the mean skinfriction distribution as well as the mean lift and drag coefficients. The goal is to provide a guideline for industrial simulations on the required resolutions for a given error tolerance. The choice of the blockstructured mesh topology in Fig. 1 was made to facilitate this purpose. This ensures all the meshes are from the family.
We define our base LES resolution to be that of the p2 solution on the coarse mesh and denote the equivalent wall units of this setting by \((\widetilde {X}_{+}^{*},\widetilde {Y}_{+}^{*},\widetilde {Z}_{+}^{*})=(20,0.96,22)\) with 0.5M DOFs. We then coarsen the resolution in the streamwise to \(2\widetilde {X}_{+}^{*}\), normal to \(2\widetilde {Y}_{+}^{*}\), and spanwise to \(2\widetilde {Z}_{+}^{*}\) directions, one direction at a time to study the influence. In the spanwise direction, we also study the \(3\widetilde {Z}_{+}^{*}\) and \(6\widetilde {Z}_{+}^{*}\) resolutions where the latter consists of only one layer in the spanwise direction.
The distribution of the mean skinfriction coefficient C_{fs} on the blade surface is shown in Fig. 11 for the considered resolutions. From this figure we can see that the \(2\widetilde {X}_{+}^{*}, 2\widetilde {Y}_{+}^{*}\), and \(6\widetilde {Z}_{+}^{*}\) resolutions failed to capture the first separation location and the separation bubble extent accurately. In particular, separation is delayed using these resolutions. On the other hand, the \(2\widetilde {Z}_{+}^{*}\) and \(3\widetilde {Z}_{+}^{*}\) resolutions accurately predicted the separation point while overestimating the length of the secondary bubble around x=0.9C_{axial}. In addition, these two resolutions captured the same peak value in the turbulent region near the trailing edge (T.E.) of the blade (x=0.95C_{axial}) but shifted slightly with respect to the DNS results. The distribution of the mean pressure coefficient on the blade surface is presented in Fig. 12. From this figure we can see that indeed the \(2\widetilde {X}_{+}^{*}, 2\widetilde {Y}_{+}^{*}\), and \(6\widetilde {Z}_{+}^{*}\) are inaccurate by a significant difference from both the DNS and the base p2 LES solutions. The other two cases, \(2\widetilde {Z}_{+}^{*}\) and \(3\widetilde {Z}_{+}^{*}\), are closer to the DNS and the base LES solutions. All cases showed very good accuracy on the pressure side except near the T.E. which indicates that high resolution is not needed for the pressure side due to the laminar attached boundary layer.
To take a closer look at the effects of these coarser resolutions, we compute the relative difference in the pressure and skinfriction coefficients with respect to the base p2 LES simulation, see Fig. 13. From this figure we can see that the difference in C_{fs} for all the cases exceeded the 5% threshold in the turbulent region near the T.E. of the blade. On the pressure side of the blade, the difference is less than 5% for all cases with the \(2\widetilde {Z}_{+}^{*}\) resolution having the lowest difference. On the other hand, the differences in the C_{p} distribution for all the cases are less than 5% except at some peaks which correspond to C_{p} approaching zero. These peaks are the consequence of division by a small number.
The PSD of the pressure signal is also considered in this section to show the effects of these coarse simulations on the pressure spectra in the wake. Figure 14 presents the PSD results of the pressure signal for the considered cases where we can see that indeed the \(2\widetilde {Z}_{+}^{*}\) and \(3\widetilde {Z}_{+}^{*}\) resolutions were able to capture the main peaks very well and follow the p2 base LES case for high St numbers. More interestingly these two resolutions were even able to capture the peak value better than the base LES simulation. This may be related also to their accurate representation in the turbulent region near the T.E. as was discussed for the C_{fs} distribution. The \(2\widetilde {X}_{+}^{*}\) and \(2\widetilde {Y}_{+}^{*}\) did not capture any peaks except a spurious one at St≈5.0 for the \(2\widetilde {Y}_{+}^{*}\) case. In addition, these two resolutions underestimated the energy content for low St number whereas the \(6\widetilde {Z}_{+}^{*}\) overestimated the PSD for almost all the captured St numbers. Based on this study, we can say that the normal as well as streamwise resolutions are more important than the spanwise resolution for this type of flow problems.
For aircraft designers, the mean lift and drag coefficients are very important performance parameters. Therefore, we conduct an additional study concerning the error in the prediction of the \(\overline {C_{L}}\) and the \(\overline {C_{D}}\) with respect to the DNS results. Table 2 shows the relative errors in addition to the nDOF in each case. From this table we can see that up to \(\widetilde {Y}_{+}=4\widetilde {Y}_{+}^{*} \approx 4.0\), one can accurately capture the mean lift and drag coefficients with only a 3.3% error. In the spanwise direction one can go further up to \(\widetilde {Z}_{+}=6\widetilde {Z}_{+}^{*} \approx 132\) with an error of 3% and only 80,000 DOF. This is a huge reduction in cost with respect to the p2 base LES simulation of 500,000 DOF. Note that the reduction in nDOF for the coarse \(\widetilde {Y}_{+}\) cases was not that large since we only double the first cell height while keeping the rest of the mesh almost the same. In these simulations we were not able to further reduce the resolution in the streamwise \(\widetilde {X}_{+}\) direction since the mesh is very coarse and a surface conforming highorder mesh was not easily obtained. Moreover, if we doubled the values of \((\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}) \approx (40,2,44)\) we still can get a very good solution with only 0.6% error, using 100,000 DOF. Finally, we show that the combination of all the coarsest resolutions at the same time resulted in a huge error for the mean \(\overline {C_{L}}\) coefficient of ≈21%.
Conclusions
In this paper, a DNS and LES study for the transitional flow over the T106C blade has been conducted using the highorder FR/CPR method. The DNS solution was established using a p3 (4^{th} order) solution on a fine mesh after a systematic h and prefinement study. In establishing convergence to the DNS solution, typical mean metrics such as mean lift and drag coefficients as well as the distribution of the skinfriction and isentropic Mach number over the blade, were utilized. Both order and mesh convergence were satisfied for the DNS solution. In addition, the PSD of the pressure and velocity spectra were used to reaffirm the convergence.
Afterwards, a LES resolution study was performed in order to assess the dependence of the mean quantities and the PSD on the values of (\(\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}\)) in wall units, i.e., streamwise, normal, and spanwise directions. It has been found that one can use a mesh with \(\left (\widetilde {X}_{+},\widetilde {Y}_{+},\widetilde {Z}_{+}\right)=(40,2,40)\) and still get a very good mean lift and drag coefficients with only 0.6% error. We were also able to show that for coarsening in one direction only, one can still get a good solution with a huge reduction in the nDOF. For instance, the \(\widetilde {Z}_{+} \approx 132\) mesh showed only a 3% error using 80,000 DOF while keeping \(\widetilde {X}_{+} \approx 20, \: \widetilde {Y}_{+} \approx 1.0\). A similar trend was found for the normal direction with \(\widetilde {Y}_{+}\) up to 4.0.
On the other hand, the pointwise difference in the skinfriction distribution exceeded 5% in the transition and turbulent regions over the blade surface for all the considered cases. For the PSD, coarsening in the spanwise direction (up to \(\widetilde {Z}_{+} \approx 60\)) had a small effect on the PSD results and was able to capture the peaks accurately.
Based on the results, we conclude that for this type of separationinduced transitional flows in turbomachinery, coarsening in the spanwise direction has a smaller effect on the mean quantities of interest and the PSD in the wake in comparison to the streamwise and normal directions. The results indicate the usefulness of such study in establishing a costeffective simulation strategy based on a predefined error threshold.
Nomenclature

Number of mesh elements

Problem dimension

Polynomial degree for highorder FR/CPR method

Number of degrees of freedom

Blade chord

Free stream velocity based on the isentropic exit conditions

Free stream pressure based on the isentropic exit conditions

Specific heats ratio of 1.4 for an ideal gas

Isentropic Mach number

Reynolds number based on the isentropic exit velocity

Pressure on the blade surface

Coefficient of pressure

Coefficient of streamwise friction

Lift coefficient

Drag coefficient

Mean mesh resolution in wall units in the blade streamwise direction normalized by p+1

Mean mesh resolution in wall units in the blade normal direction normalized by p+1

Mean mesh resolution in wall units in the spanwise direction normalized by p+1

Characteristic time

Frequency in Hz

Strouhal number

Fourier transformed amplitude of the onesided spectrum for a time signal G

Power spectral density

Flux reconstruction or correction procedure via reconstruction method

Large eddy simulations

Direct numerical simulations

Reynolds averaged NavierStokes equations
Availability of data and materials
All data generated or analyzed during this study are included in this published article. Parts of the data and materials are available upon request.
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Acknowledgements
The authors would like to acknowledge the financial support by AFOSR under grant FA95501610128 and US Army Research Office under grant W911NF1510505.
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AFOSR grant (FA95501610128), US Army Research Office grant (W911NF1510505).
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Alhawwary, M., Wang, Z. On the mesh resolution of industrial LES based on the DNS of flow over the T106C turbine. Adv. Aerodyn. 1, 21 (2019). https://doi.org/10.1186/s4277401900236
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Keywords
 Direct numerical simulations
 Large eddy simulations
 Transitional flows
 Highorder FR/CPR
 T106C
 Skinfriction
AMS Subject Classification
 76F65; 76F06; 65M60; 65M70