Abstract The aim of this work is twosided. Firstly, experimental results obtained for numerous sets of airfoil measurements (mainly intended for wind

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1 Wind Turbine Airfoil Catalogue Risfi R 8(EN) Franck Bertagnolio, Niels Sfirensen, Jeppe Johansen and Peter Fuglsang Risfi National Laboratory, Roskilde, Denmark August
2 Abstract The aim of this work is twosided. Firstly, experimental results obtained for numerous sets of airfoil measurements (mainly intended for wind turbine applications) are collected and compared with computational results from the D NavierStokes solver, as well as results from the panel method code. Secondly, weareinterested in validating the code and finding out for which airfoils it does not perform well compared to the experiments, as well as why, when it does so. The airfoils are classified according to the agreement between the numerical results and experimental data. A study correlating the available data and this classification is performed. It is found that transition modelling is to a large extent responsible for the poor quality of the computational results for most of the considered airfoils. The transition model mechanism that leads to these discrepancies is identified. Some advices are given for elaborating future airfoil design processes that would involve the numerical code in particular, and transition modelling in general. ISBN ISBN 87 9 (Internet) ISSN 8 Print: Pitney Bowes Management Services Danmark A/S
3 Contents Introduction NACA Wing Sections. Method. Results NACA  9 NACA 8 NACA  7 NACA  NACA 8 NACA  9 NACA  NACA  7 NACA  NACA  NACA  and NACA  Airfoils (VELUX Measurements) 9. Method 9. Results 9 NACA (V) NACA (V) NACA  Airfoil (VELUX Measurements) 8. Method 8. Results 8 RISχA Family Airfoils. Method. Results RISχA8 RISχA 8 RISχA 7 FFAW Airfoil 7. Method 7. Results 7 FFAW, Fixed Transition 77 FFAW, Free Transition 8 7 FFAW and FFAW Airfoils 8 7. Method 8 7. Results 8 FFAW 8 FFAW 9 Risfi R 8(EN)
4 8 S89 and S8 Airfoils 9 8. Method 9 8. Results 9 S89 9 S FXS9V Airfoil 9. Method 9. Results DU 9W and DU 9W Airfoils 8. Method 8. Results 8 DU 9W 9 DU 9W AAirfoil 7. Method 7. Results 7 Analysis of the Collected Results. Quantitative criteria. Classifying the airfoils. Interpretation of the selected airfoils data. Study of the transition and stall behaviors. Conclusions regarding the numerical code performances and airfoil design Conclusion 9 APPENDICES A LS() and LS()7 Airfoils References Risfi R 8(EN)
5 Introduction The aim of this report is to provide a catalogue of results for a wide range of wind turbine airfoils. These results are obtained from numerical simulations with the D incompressible NavierStokes solver (see [8, 9, ] for a detailed description of the numerical code). They are compared with experimental data, when these are available. The results are also compared with the code, which is based on a panel method combined with a viscous boundary layer formulation [9]. This work has several objectives. Firstly, it will permit to qualitatively evaluate the computational code and its performances. Secondly, by comparing the results obtained for the wide range of airfoils, on one hand it will be possible to give a better idea of the difficulties that can be faced when simulating certain types of airfoil, and on the other hand to identify the airfoil types that can be correctly simulated by the numerical model. Finally, it will provide a database of airfoil characteristics, that can be used in wind turbine design. In each of the sections where experimental and computational results are reported, there is a short introductory text describing the experimental facilities, as well as some relevant informations about the computations. Several airfoils can be included in the same section if they were experimentally measured during the same campaign. Measurements for some of the NACA wing sections were obtained in the VELUX wind tunnel [], whereas others were collected from the book by Abbott and von Doenhoff []. In the present report, the former ones are distinguished from the latter by adding (V) at the end of their respective airfoil names whenever necessary (e.g. NACA  was obtained from [], and NACA (V) was measured in the VELUX wind tunnel). The meshes that were used for computations are not drawn for every single airfoil. However, the one used for the NACA  in section is depicted. The general aspect of all the meshes used herein is very similar, the only difference in the mesh generation being the airfoil shape. All meshes were generated with the grid generator HypGridD []. The code is used in its standard version with panels distributed on the airfoil surface. The viscous boundary layer and wake options are activated. The Reynolds number is set to the same value as in the NavierStokes computations. An OrrSommerfeld transition criterion is used to simulate free transition. However, for cases where the experiment has been performed with a device triggering transition, fixed transition is enforced at the same chordwise location. The report is organized as follows. In sections to, the experimental and computational data are reported for the numerous airfoils. In section, the results are analysed by classifying the airfoils according to agreements or discrepancies between experiments and computations. Then, conclusions are drawn regarding the performances of the numerical code. The main conclusions of this work are reported in the last section. Additional airfoils will progressively be included in the appendices in future releases of this report. Risfi R 8(EN)
6 NACA Wing Sections This section is dedicated to the computation of several airfoils of the NACA wing section family. The computational data obtained with will be compared to the measurements performed at NASA in a lowturbulence pressure tunnel []. These measurements are reported in the book by Abbott and von Doenhoff []. Three subfamilies of NACA wing sections are investigated: NACA, NACA and NACA. They differ from each other by the chordwise position of minimum pressure. Then, a third digit indicates the design lift coefficient. The airfoils can finally be distinguished by their thickness, which is given by the last digits. Among the numerous possibilities in the different families, only the following airfoils are considered: NACA , NACA 8, NACA  NACA , NACA 8, NACA  NACA , NACA  NACA , NACA  It must be noted that most of these airfoils are used on wind turbines. For all the cases that are presented in this section, the Reynolds number of the experiment (and the computations) was Re =:.. Method Cmeshes were used for all the computations with 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. Further refinements of the grid didn't significantly improve the results. The mesh used for the NACA  airfoil, and details of regions of interest, are displayed on Figures . As it can be seen, the mesh lines were extended in the wake of the trailing edge in order to stabilize the computations. The computations were performed with the SUDSscheme for convective terms. The k! SST turbulence model by Menter was used for the turbulent viscosity []. The transition model by Michel [7] was used for simulating the free transition, together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency. Numerical results were obtained with stationary computations.. Results Results are presented as lift, drag and pitching moment coefficients as function of angle of attack, and also pressure and skin friction distributions at various angles are shown. There was an overall good agreement between the experimental data and the computational results. However, for some of the airfoils, there exists a shift in the angle of attack between experiments and computations in the linear region, where simulations were expected to perform well. This shift can be observed on the lift curve for the following airfoils: NACA , NACA , NACA 8, NACA , NACA , on Figures 8, respectively. Moreover, similar results were found using the panel method. In order to assess that the numerical code was not responsible for these discrepancies, an experimentthat was performed with the same airfoil as NACA  in another wind tunnel was considered in section. Risfi R 8(EN)
7 Figure. Mesh around the NACA  airfoil  Full view Figure. Mesh around the NACA  airfoil  Closer view of the airfoil Risfi R 8(EN) 7
8 Figure. Mesh around the NACA  airfoil  Closer view of the leading edge Figure. Mesh around the NACA  airfoil  Closer view of the trailing edge 8 Risfi R 8(EN)
9 NACA ... y/chord Figure.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN) 9
10 Drag Coefficient Figure 7. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
11 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 9. Distributions (NACA ) Risfi R 8(EN)
12 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
13 NACA y/chord Figure.NACA 8 Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA 8, []) Risfi R 8(EN)
14 Drag Coefficient Figure. Drag Coefficient Curve (NACA 8, [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA 8, []) Risfi R 8(EN)
15 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA 8) Risfi R 8(EN)
16 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA 8) Risfi R 8(EN)
17 NACA ... y/chord Figure 7.NACA  Airfoil.8... Lift Coefficient.8... Figure 8. Lift Coefficient Curve (NACA , []) Risfi R 8(EN) 7
18 Drag Coefficient Figure 9. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) 8 Risfi R 8(EN)
19 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN) 9
20 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
21 NACA ... y/chord Figure.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN)
22 Drag Coefficient Figure. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
23 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 7. Distributions (NACA ) Risfi R 8(EN)
24 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 8. Distributions (NACA ) Risfi R 8(EN)
25 NACA y/chord Figure 9.NACA 8 Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA 8, []) Risfi R 8(EN)
26 Drag Coefficient Figure. Drag Coefficient Curve (NACA 8, [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA 8, []) Risfi R 8(EN)
27 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA 8) Risfi R 8(EN) 7
28 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA 8) 8 Risfi R 8(EN)
29 NACA ... y/chord Figure.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN) 9
30 Drag Coefficient Figure 7. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
31 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 9. Distributions (NACA ) Risfi R 8(EN)
32 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
33 NACA ... y/chord Figure.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN)
34 Drag Coefficient Figure. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
35 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
36 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
37 NACA ... y/chord Figure 7.NACA  Airfoil.8... Lift Coefficient.8... Figure 8. Lift Coefficient Curve (NACA , []) Risfi R 8(EN) 7
38 Drag Coefficient Figure 9. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) 8 Risfi R 8(EN)
39 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN) 9
40 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN)
41 NACA ... y/chord Figure.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN)
42 Drag Coefficient Figure. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
43 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 7. Distributions (NACA ) Risfi R 8(EN)
44 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure 8. Distributions (NACA ) Risfi R 8(EN)
45 NACA ... y/chord Figure 9.NACA  Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA , []) Risfi R 8(EN)
46 Drag Coefficient Figure. Drag Coefficient Curve (NACA , [])..9.8 Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (NACA , []) Risfi R 8(EN)
47 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) Risfi R 8(EN) 7
48 (a) ff = o (b) ff = o (c) ff = o (d) ff = o (e) ff = o (f) ff =8 o Figure. Distributions (NACA ) 8 Risfi R 8(EN)
49 NACA  and NACA  Airfoils (VELUX Measurements) These airfoils belong to the NACA wing section family. They were measured in the VELUX wind tunnel [], which has an open test section. The testing facility is described in detail by Fuglsang et al []. The Reynolds number of the experiment (and for the computations) was equal to : for the NACA  airfoil, and : for the NACA . Note that these are the freestream Reynolds numbers that have been measured in the wind tunnel.. Method The Cmeshes used for the computations had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms. The k! SST turbulence model by Menter was used for the turbulent viscosity[]. As the turbulence level was relatively high in the wind tunnel, it was expected that a fully turbulent computation might give better results. Therefore, both fully turbulent simulations and computations with the Michel transition model [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency, were conducted. Numerical results were obtained with stationary computations. It must be noted that for the first airfoil, due to large oscillations of the results for high angles of attack in steady state computations with transition model, the simulations for these large angles were performed in an unsteady mode in order to enhance the numerical stability of the method (with a nondimensional time step equal to ). The influence can clearly be seen on the pressure coefficient on Figs.9(def) and the skin friction coefficient (Figs.7(def)). The same problem was encountered for the second airfoil only for the highest angle of attack (ff = : o )forwhich pressure and skin friction coefficients are not presented.. Results As for the NACA  airfoil, the computational results and experimental data were in good agreement, except for after stall. As it can be seen on Figs. 78, the simulations were quite insensitive to the transition modelling in the linear region. It must be noted that the experiment and simulations were in good agreement in this region, when it was not the case with the very same airfoil measured in another wind tunnel (see section ). As for the NACA  airfoil, experiment and simulations were in rather good agreement in the linear region, but computations predicted a higher maximum lift. Risfi R 8(EN) 9
50 NACA (V)... y/chord Figure.NACA  Airfoil..  Fully turbulent  Transition model. Lift Coefficient.8... Figure. Lift Coefficient Curve (NACA (V), []) Risfi R 8(EN)
51 .  Fully turbulent  Transition model. Drag Coefficient... Figure 7. Drag Coefficient Curve (NACA (V), [])..8  Fully turbulent  Transition model.. Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (NACA (V), []) Risfi R 8(EN)
52  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =:7 o (b) ff =:8 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =: o (d) ff =:78 o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =7:7 o (f) ff =9:9 o Figure 9. Distributions (NACA (V), []) Risfi R 8(EN)
53 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =:7 o (b) ff =:8 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =: o (d) ff =:78 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =7:7 o (f) ff =9:9 o Figure 7. Distributions (NACA (V)) Risfi R 8(EN)
54 NACA (V)... y/chord Figure 7.NACA  Airfoil.8.  Fully turbulent  Transition model.. Lift Coefficient.8... Figure 7. Lift Coefficient Curve (NACA (V), []) Risfi R 8(EN)
55 ..  Fully turbulent  Transition model.. Drag Coefficient..... Figure 7. Drag Coefficient Curve (NACA (V), [])..  Fully turbulent  Transition model.8. Moment Coefficient Figure 7. Pitching Moment Coefficient Curve (NACA (V), []) Risfi R 8(EN)
56  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =:9 o (b) ff =8: o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =: o (d) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =:9 o (f) ff =7:9 o Figure 7. Distributions (NACA (V), []) Risfi R 8(EN)
57 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =:9 o (b) ff =8: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =: o (d) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =:9 o (f) ff =7:9 o Figure 7. Distributions (NACA (V)) Risfi R 8(EN) 7
58 NACA  Airfoil (VELUX Measurements) This airfoil belongs to the NACA wing section family. It has been measured in the VELUX wind tunnel [], which has an open test section. The testing facility is described in detail by Fuglsang et al []. The Reynolds number of the experiment (and for the computations) wasequalto:.. Method The Cmesh used for the computation had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms. The k! SST turbulence model by Menter was used for the turbulent viscosity[]. As the turbulence level was relatively high in the wind tunnel, it was expected that a fully turbulent computation might give better results. Therefore, both fully turbulent simulations and computations with the Michel transition model [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency, were conducted. Numerical results were obtained with stationary computations.. Results Neither the fully turbulent computations, nor the simulations with transition model, were able to correctly estimate the experimental data. Moreover, the discrepancies are quite large. 8 Risfi R 8(EN)
59 NACA (V)... y/chord Figure 77.NACA  Airfoil..  Fully turbulent  Transition model. Lift Coefficient.8... Figure 78. Lift Coefficient Curve (NACA (V), []) Risfi R 8(EN) 9
60 ..  Fully turbulent  Transition model. Drag Coefficient Figure 79. Drag Coefficient Curve (NACA (V), [])...  Fully turbulent  Transition model.9 Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (NACA (V), []) Risfi R 8(EN)
61  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =:8 o (b) ff =8:8 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =: o (d) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =:9 o (f) ff =:7 o Figure 8. Distributions (NACA (V), []) Risfi R 8(EN)
62 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =:8 o (b) ff =8:8 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =: o (d) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =:9 o (f) ff =:7 o Figure 8. Distributions (NACA (V)) Risfi R 8(EN)
63 RISχA Family Airfoils In this section, three airfoils of the RISχA family were tested. These airfoils were developed and optimized at Risfi National Laboratory for use on wind turbines []. The airfoils were tested in the VELUX wind tunnel, which has an open test section with a background turbulence level of %. It is described in detail by Fuglsang et al []. All tests were carried out at the highest possible Reynolds number Re =: (see [] for more details about the measurements). The following three airfoils were studied: RISχA8 RISχA RISχA. Method Although these airfoils have a blunt trailing edge, Cmeshes were used for all the computations. Therefore, the airfoils were slightly sharpened at the trailing edge. The meshes had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The SUDSscheme was used for the convective terms in all computations. Turbulence was simulated by the k! SST model by Menter []. Both fully turbulent computations and computations with the transition model by Michel [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency, were performed. The reason for this was that the fully turbulent computations were expected to give rather good results as the background turbulence level in the wind tunnel was relatively high. This might trigger an early transition to turbulence in the airfoil boundary layer. Numerical results were obtained with stationary computations.. Results The computational results showed relative good agreement with the experiments for the three airfoils. In the linear region, the simulations with transition model were closer to the experimental data, whereas the fully turbulent computations were closer in the stalled region. Simulations with transition model predicted stall at a higher angle of attack than the experiment and overestimated the maximum lift. Risfi R 8(EN)
64 RISχA8... y/chord Figure 8. RISχA8 Airfoil.8.  Fully turbulent  Transition model.. Lift Coefficient.8... Figure 8. Lift Coefficient Curve (RISχA8, []) Risfi R 8(EN)
65 Fully turbulent  Transition model. Drag Coefficient Figure 8. Drag Coefficient Curve (RISχA8, [])..  Fully turbulent  Transition model. Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (RISχA8, []) Risfi R 8(EN)
66  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =:7 o (b) ff =7:9 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =:7 o (d) ff =:7 o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =: o (f) ff =8:9 o Figure 87. Distributions (RISχA8, []) Risfi R 8(EN)
67 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =:7 o (b) ff =7:9 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =:7 o (d) ff =:7 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =: o (f) ff =8:9 o Figure 88. Distributions (RISχA8) Risfi R 8(EN) 7
68 RISχA... y/chord Figure 89. RISχA Airfoil.8.  Fully turbulent  Transition model.. Lift Coefficient.8... Figure 9. Lift Coefficient Curve (RISχA, []) 8 Risfi R 8(EN)
69 Fully turbulent  Transition model. Drag Coefficient Figure 9. Drag Coefficient Curve (RISχA, [])..  Fully turbulent  Transition model. Moment Coefficient Figure 9. Pitching Moment Coefficient Curve (RISχA, []) Risfi R 8(EN) 9
70  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =: o (b) ff =8:9 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =: o (d) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =: o (f) ff =7:88 o Figure 9. Distributions (RISχA, []) 7 Risfi R 8(EN)
71 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =: o (b) ff =8:9 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =: o (d) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =: o (f) ff =7:88 o Figure 9. Distributions (RISχA) Risfi R 8(EN) 7
72 RISχA... y/chord Figure 9. RISχA Airfoil.8.  Fully turbulent  Transition model.. Lift Coefficient.8... Figure 9. Lift Coefficient Curve (RISχA, []) 7 Risfi R 8(EN)
73 Fully turbulent  Transition model. Drag Coefficient Figure 97. Drag Coefficient Curve (RISχA, [])..  Fully turbulent  Transition model. Moment Coefficient Figure 98. Pitching Moment Coefficient Curve (RISχA, []) Risfi R 8(EN) 7
74  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =:97 o (b) ff =8:8 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =:7 o (d) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =:9 o (f) ff =9: o Figure 99. Distributions (RISχA, []) 7 Risfi R 8(EN)
75 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =:97 o (b) ff =8:8 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =:7 o (d) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =:9 o (f) ff =9: o Figure. Distributions (RISχA) Risfi R 8(EN) 7
76 FFAW Airfoil The FFAW airfoil manufactured and equipped at FFA (The Aeronautical Research Institute of Sweden) was investigated. It is a % thickness airfoil. It was tested in the low speed wind tunnel L (located at KTH, Royal Institute of Technology, Stockholm) with a turbulence intensity of.% [, 7]. The Reynolds number of the experiment was Re =:8. Two sets of measurements were used herein. The first was obtained with an adhesive tape at the airfoil upper and lower side at x=chord = %, in order to trigger boundary layer transition at these locations. Transition was let free for the second one.. Method A Cmesh was used to compute the flow around this airfoil with 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms, together with the k! SST turbulence model by Menter [] for the turbulent viscosity. The transition was fixed at x=chord = % on both sides of the airfoil when comparing with the first set of measurements. The transition model by Michel [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency, was used when comparing with freetransition measurements. Numerical results were obtained with stationary computations.. Results For both cases (fixed and free transition), the computational results matched the experimental data in the linear region, but stall was predicted at a too high angle of attack, and a greater maximum lift was computed. However, results were in slightly better agreement for the case with free transition. 7 Risfi R 8(EN)
77 FFAW, Fixed Transition... y/chord Figure.FFAW Airfoil.8... Lift Coefficient.8... Figure. Lift Coefficient Curve (FFAW, Fixed Transition, [7]) Risfi R 8(EN) 77
78 .. Drag Coefficient.. Figure. Drag Coefficient Curve (FFAW, Fixed Transition, [7])... Moment Coefficient Figure. Pitching Moment Coefficient Curve (FFAW, Fixed Transition, [7]) 78 Risfi R 8(EN)
79 (a) ff =: o (b) ff =7:99 o (c) ff =:7 o (d) ff =:98 o (e) ff =7: o (f) ff =: o Figure. Distributions (FFAW, Fixed Transition, [7]) Risfi R 8(EN) 79
80 (a) ff =: o (b) ff =7:99 o (c) ff =:7 o (d) ff =:98 o (e) ff =7: o (f) ff =: o Figure. Distributions (FFAW, Fixed Transition) 8 Risfi R 8(EN)
81 FFAW, Free Transition... y/chord Figure 7.FFAW Airfoil.8... Lift Coefficient.8... Figure 8. Lift Coefficient Curve (FFAW, Free Transition, [7]) Risfi R 8(EN) 8
82 .. Drag Coefficient.. Figure 9. Drag Coefficient Curve (FFAW, Free Transition, [7]).. Pitching Moment Coefficient Figure. Pitching Moment Coefficient Curve (FFAW, Free Transition, [7]) 8 Risfi R 8(EN)
83 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =7: o (f) ff =: o Figure. Distributions (FFAW, Free Transition) Risfi R 8(EN) 8
84 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =7: o (f) ff =: o Figure. Distributions (FFAW, Free Transition) 8 Risfi R 8(EN)
85 7 FFAW and FFAW Airfoils These two airfoils have been designed at FFA (The Aeronautical ResearchInstitute of Sweden) by Björk []. They are relatively thick and have been used on the inboard part of different Danish wind turbine blades. Measurements were carried out in the VELUX wind tunnel [], which has an open test section. The testing facility is described in detail by Fuglsang et al []. The Reynolds number was equal to : for both airfoils measurement campaigns. 7. Method The Cmeshes used for the computation had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms. As the turbulence level was relatively high in the wind tunnel, it was expected that a fully turbulent computation might give better results. Therefore, both fully turbulent simulations and computations with the Michel transition model [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency,were conducted. The k! SST turbulence model by Menter [] was used for the turbulent viscosity. Numerical results were obtained with stationary computations. 7. Results For both airfoils, the computational results and experimental data were in rather good agreement in the linear region. However, the fully turbulent computations predicted stall at a correct angle of attack, contrary to the simulations with free transition that predicted stall at a much higher angle of attack. Risfi R 8(EN) 8
86 FFAW... y/chord Figure.FFAW Airfoil.8.  Fully turbulent  Transition model.. Lift Coefficient.8... Figure. Lift Coefficient Curve (FFAW, []) 8 Risfi R 8(EN)
87 .  Fully turbulent  Transition model. Drag Coefficient.. Figure. Drag Coefficient Curve (FFAW, [])...  Fully turbulent  Transition model. Moment Coefficient Figure. Pitching Moment Coefficient Curve (FFAW, []) Risfi R 8(EN) 87
88  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =: o (b) ff =9:89 o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =:9 o (d) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =7:888 o (f) ff =:88 o Figure 7. Distributions (FFAW, []) 88 Risfi R 8(EN)
89 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =: o (b) ff =9:89 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =:9 o (d) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =7:888 o (f) ff =:88 o Figure 8. Distributions (FFAW) Risfi R 8(EN) 89
90 FFAW... y/chord Figure 9.FFAW Airfoil.8  Fully turbulent  Transition model.. Lift Coefficient Figure. Lift Coefficient Curve (FFAW, []) 9 Risfi R 8(EN)
91 ..  Fully turbulent  Transition model. Drag Coefficient..... Figure. Drag Coefficient Curve (FFAW, []) Fully turbulent  Transition model. Moment Coefficient Figure. Pitching Moment Coefficient Curve (FFAW, []) Risfi R 8(EN) 9
92  Fully turbulent  Transition model  Fully turbulent  Transition model (a) ff =: o (b) ff =: o  Fully turbulent  Transition model  Fully turbulent  Transition model (c) ff =9: o (d) ff =:8 o  Fully turbulent  Transition model  Fully turbulent  Transition model (e) ff =: o (f) ff =: o Figure. Distributions (FFAW, []) 9 Risfi R 8(EN)
93 .  Fully turbulent  Transition model.  Fully turbulent  Transition model (a) ff =: o (b) ff =: o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (c) ff =: o (d) ff =:8 o.  Fully turbulent  Transition model.  Fully turbulent  Transition model (e) ff =: o (f) ff =: o Figure. Distributions (FFAW) Risfi R 8(EN) 9
94 8 S89 and S8 Airfoils The S89 airfoil is a % thick wind turbine airfoil that has been designed at National Renewable Energy Laboratory (NREL), Colorado, USA, by Somers []. The two primary design criteria were restrained maximum lift, insensitive to surface roughness, and low profile drag. The S8 airfoil is a % thick wind turbine airfoil that has been designed at National Renewable Energy Laboratory (NREL), Colorado, USA, by Somers []. The first objective was to achieve a maximum lift coefficient of at least. for a Reynolds numberof:. The second objective was to obtain low profile drag coefficients over the range of lift coefficients from. to. for the same Reynolds number. The experiments were carried out at the lowturbulence wind tunnel at Delft University of Technology, The Netherlands. The Reynolds number of the experiments was Re = :, and the experimental results exposed herein were obtained with free transition. Numerical results were obtained with stationary computations. 8. Method The Cmesh used for the computations had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms, the k! SST turbulence model by Menter [] for the turbulent viscosity, and the transition model bymichel [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency. 8. Results There was a good agreement between experimental data and computational results in the linear region. A higher maximum lift was computed in the stalled region. 9 Risfi R 8(EN)
95 S89... y/chord Figure.S89Airfoil.. Lift Coefficient.8... Figure. Lift Coefficient Curve (S89, Delft University of Technology) Risfi R 8(EN) 9
96 ... Drag Coefficient.8... Figure 7. Drag Coefficient Curve (S89, Delft University of Technology)..8 Moment Coefficient... Figure 8. Pitching Moment Coefficient Curve (S89, Delft University of Technology) 9 Risfi R 8(EN)
97 (a) ff =: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure 9. Distributions (S89) Risfi R 8(EN) 97
98 (a) ff =: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure. Distributions (S89) 98 Risfi R 8(EN)
99 S8... y/chord Figure.S8Airfoil... Lift Coefficient.8... Figure. Lift Coefficient Curve (S8, Delft University of Technology) Risfi R 8(EN) 99
100 ... Drag Coefficient.8... Figure. Drag Coefficient Curve (S8, Delft University of Technology)... Moment Coefficient Figure. Pitching Moment Coefficient Curve (S8, Delft University of Technology) Risfi R 8(EN)
101 (a) ff =: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure. Distributions (S8) Risfi R 8(EN)
102 (a) ff =: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure. Distributions (S8) Risfi R 8(EN)
103 9 FXS9V Airfoil The FXS9V airfoil is a 9% thick airfoil designed by Althaus and Wortmann []. It is a typical laminar airfoil where transitional effects are large since laminar flow is present over the majority of the airfoil surface. The Reynolds number of the experiment was :. The experiment was carried out in the Laminar Wind Tunnel at the Institut for Aerodynamics and Gasdynamics in Stuttgart []. 9. Method The Cmesh used for the computation had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms, the k! SST turbulence model by Menter [] for the turbulent viscosity, and the transition model bymichel [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency. Numerical results were obtained with stationary computations. 9. Results There was a very good agreement between the experiment and the computations concerning the lift. The drag was slightly overestimated by the computations. Risfi R 8(EN)
104 FXS9V... y/chord Figure 7. FXS9V Airfoil... Lift Coefficient.8... Figure 8. Lift Coefficient Curve (FXS9V, []) Risfi R 8(EN)
105 ..8 Drag Coefficient... Figure 9. Drag Coefficient Curve (FXS9V, []).. Moment Coefficient..8.. Figure. Pitching Moment Coefficient Curve (FXS9V) Risfi R 8(EN)
106 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure. Distributions (FXS9V) Risfi R 8(EN)
107 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =: o (f) ff =8: o Figure. Distributions (FXS9V) Risfi R 8(EN) 7
108 DU 9W and DU 9W Airfoils The % thick wind turbine airfoil DU 9W was designed by Timmer []. Its design goals for the laminar case were a peak lift coefficient of about., relatively smooth stall and insensivity to roughness. The measurements were performed in the lowspeed lowturbulence wind tunnel of the Faculty of Aerospace Engineering of Delft University []. The results presented herein were obtained at a Reynolds number of : with a smooth airfoil surface. The % thick wind turbine airfoil DU 9W was designed by Timmer and wind tunnel tested in the same low speed wind tunnel at Delft University of Technology.. Method The Cmesh used for the computation had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms, the k! SST turbulence model by Menter [] for the turbulent viscosity, and the transition model bymichel [7], together with the empirical function given by Chen and Thyson [8] for modelling the turbulence intermittency. Numerical results were obtained with stationary computations.. Results There was a rather good agreementbetween experiments and computations in the linear region, but the lift was overpredicted by the computations in deep stall. 8 Risfi R 8(EN)
109 DU 9W... y/chord Figure. DU 9W Airfoil... Lift Coefficient.8... Figure. Lift Coefficient Curve (DU 9W, []) Risfi R 8(EN) 9
110 ... Drag Coefficient Figure. Drag Coefficient Curve (DU 9W, []).. Moment Coefficient....9 Figure. Pitching Moment Coefficient Curve (DU 9W, []) Risfi R 8(EN)
111 (a) ff =7:8: o (b) ff =9:7 o (c) ff =:7 o (d) ff =: o (e) ff =:9 o (f) ff =: o Figure 7. Distributions (DU 9W, []) Risfi R 8(EN)
112 (a) ff =7:8 o (b) ff =9:7 o (c) ff =:7: o (d) ff =: o (e) ff =:9 o (f) ff =: o Figure 8. Distributions (DU 9W) Risfi R 8(EN)
113 DU 9W... y/chord Figure 9. DU 9W Airfoil... Lift Coefficient.8... Figure. Lift Coefficient Curve (DU 9W, Delft University of Technology) Risfi R 8(EN)
114 ... Drag Coefficient.8... Figure. Drag Coefficient Curve (DU 9W, Delft University of Technology)... Moment Coefficient Figure. Pitching Moment Coefficient Curve (DU 9W, Delft University of Technology) Risfi R 8(EN)
115 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =8: o (f) ff =: o Figure. Distributions (DU 9W) Risfi R 8(EN)
116 (a) ff =8: o (b) ff =: o (c) ff =: o (d) ff =: o (e) ff =8: o (f) ff =: o Figure. Distributions (DU 9W) Risfi R 8(EN)
117 AAirfoil The AAirfoil was chosen as a test case for validating several numerical codes by the partners of the ECARP project []. s were carried out in the F and F wind tunnels at ONERA/FAUGA. The Reynolds number of the experiment was Re =:.. Method The Cmesh used for the computation had 8 cells in the direction along the airfoil, of them being on the airfoil, and cells in the direction away from the airfoil. The nondimensional height of the cell at the airfoil was. The computations were performed with the SUDSscheme for the convective terms, and the k! SST turbulence model by Menter [] for the turbulent viscosity. The analysis of the measurements shows that the transition on the upper side of the airfoil occured at a fixed location x=chord = :. Therefore, the transition was also fixed in the computations. On the lower side, the transition was fixed both in the experiment and the computations at x=chord = :.. Results There was a good agreement between the experiment and the computations in the linear region. Higher maximum lift was predicted by the computations. exhibits a strange and unexplainable behavior for a small range of angles of attack before stall. Risfi R 8(EN) 7
118 AAirfoil... y/chord Figure.AAirfoil.8.. Lift Coefficient Figure. Lift Coefficient Curve (AAirfoil, []) 8 Risfi R 8(EN)
119 ..8.. Drag Coefficient Figure 7. Drag Coefficient Curve (AAirfoil, [])... Moment Coefficient Figure 8. Pitching Moment Coefficient Curve (AAirfoil) Risfi R 8(EN) 9
120 (a) ff =: o (b) ff =: o (c) ff =7: o (d) ff =8: o (e) ff =: o Figure 9. Distributions (AAirfoil, []) Risfi R 8(EN)
121 (a) ff =: o (b) ff =: o (c) ff =7: o (d) ff =8: o (e) ff =: o Figure. Distributions (AAirfoil, []) Risfi R 8(EN)
122 Analysis of the Collected Results In this section, an analysis of the data that have been collected for the numerous airfoils is attempted. The main objective is to be able to evaluate a priori how good the numerical code will perform for a given airfoil. Firstly, quantitative values assessing the agreement between experimental data and computational results from are calculated. Secondly, airfoils for which the numerical code can be considered as performing well and those for which it performs poorly are sorted with the help of those values. Finally, some conclusions can be drawn concerning the ability of the numerical code to simulate the flow around certain types of airfoils. These conclusions can give some hints for the design of future airfoils, as far as the numerical code may beinvolved as atoolinthe design process; but also to a greater extent as they can reveal characteristic facts about the actual flow.. Quantitative criteria Quantitative values measuring the discrepancies between experimental data and computational results for each airfoil are gathered in Table, p.7. For each airfoil, the following four criterionvalues are computed:. The difference of lift between experiment and computations averaged over the linear region, expressed in percentage relatively to the maximum experimental lift coefficient, is calculated.. Theangleofattack for which stall occurs is considered. The angle for which a maximum of lift coefficient is first reached is reported. Then, the difference between the experimental and the computational values is evaluated in percentage relatively to the corresponding experimental angle (Note that in this case, the maximum lift location is searched close after the linear region, even if the lift coefficient grows again after stall, as it can be the case for some experiments).. The difference of maximum lift at the previously detected two points is evaluated in percentage relatively to the experimental maximum lift.. The maximum difference of lift (at a given angle of attack) in the stalled region is expressed in percentage relatively to the maximum experimental lift. It should be noted that, when both fully turbulent computations and simulations with transition model were available, the latter ones were used for calculating these four values.. Classifying the airfoils In this second step of the analysis, the airfoils for which the results obtained with are in good agreement with the experimental data are first collected. Then the airfoils for which results are in large disagreement with the experiments are collected. To select the airfoils that perform well, the three following conditions using the previously computed criterionvalues are evaluated: ffl The first criterionvalue is below % Risfi R 8(EN)
123 ffl The second criterionvalue is below % ffl The third or fourth criterionvalue is below % The airfoils that fulfil all these criteria are considered to be the ones that perform well. Note that the first condition is assumed to be satisfied for all the NACA airfoils in section (see the comments in section.). The limiting percentages have been chosen in order to make a clear distinction between the airfoils. At the same time, the limits are considered to be sensible as for the respective importance of the several criteria. These airfoils can be roughly classified from the best one to the worst one as: ) FXS9V ) NACA  ) NACA  ) NACA (V) ) NACA (V) ) NACA 8 7) NACA 8 8) NACA FFAW 9) S8 They are depicted in Fig.. Note that the NACA  and NACA  airfoils have not been included even though they fulfil the above criteria. It was considered that they would not significantly improve the amount of data involved with airfoils from the NACA wing section family that have been already selected for the next step of the analysis. The airfoils that perform poorly are selected next. They are defined to be the ones for which strictly more than two of the following conditions are satisfied: ffl The first criterionvalue is over % ffl The second criterionvalue is over % ffl The third criterionvalue is over % ffl The fourth criterionvalue is over % These airfoils can be roughly classified from the worst one to the best one as: ) NACA (V) ) FFAW (Fixed Tr.) ) RISχA ) NACA  ) NACA  ) NACA  They are depicted in Fig... Interpretation of the selected airfoils data It is now attempted to correlate some characteristics of the previously selected airfoils with the quality of the results. It would be interesting to relate the performance of the code to purely geometrical characteristics of the airfoils. Therefore, both the maximum relative thickness and the maximum curvature near the leading edge of the selected airfoils are reported in Table, p.7. The curvatures of the airfoils surfaces in the vicinity of the leading edge are plotted on Figs.(a) and (b). It can be concluded that poorlyperforming airfoils are somewhat thicker than wellperforming airfoils, whereas the latter ones have a rather more curved leading edge. However, these conclusions highlight a general tendency, but these are not clearly decisive factors. Risfi R 8(EN)
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