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Aerodynamic characteristics of a square cylinder with corner fins
Advances in Bridge Engineering volume 2, Article number: 20 (2021)
Abstract
This paper investigates the effect of fitting fins at the corners of a square cylinder on aerodynamic characteristics of the cylinder via wind tunnel tests and large eddy simulations (LES). Although it has been recognized that the corner fins have a remarkable effect on aerodynamic characteristics of a square cylinder, no study has been carried out to systematically evaluate this effect and reveal the underlying mechanism. Three types of corner fin configurations, i.e. fins fitted only to the leading corners, fins fitted only to the trailing corners, and fins fitted to both leading and trailing corners were studied. It was found that the corner fins significantly influence aerodynamic characteristics, such as mean drag coefficient, fluctuating lift coefficient, and vortex shedding of the cylinder. The influences of these corner fin configurations are very different. In general, the leading and trailing fins have an opposite effect on these characteristics. The mechanisms underlying these effects were clarified based on the flow regime visualized via LES. The interesting findings have practical significances not only for reducing aerodynamic forces and windinduced vibration of infrastructures, but also for enhancing windinduced vibrationbased energy harvesting.
Introduction
Aerodynamic modification on bluff bodies such as square prism and circular cylinder has attracted extensive studies in the past decades due to its practical significance for either reducing windinduced vibration of engineering structures or enhancing the vibration of wind energy harvesters.
The overwhelming majority of these studies concentrated on aerodynamic modifications to reduce windinduced vibration for ensuring structural safety (Gao et al. 2017; Tang et al. 2019; Xu et al. 2014). The common strategies to achieve this goal include jet flow control (Chen et al. 2015), slotting corners (Kwok et al. 1988; Kwok and Bailey 1987), fitting solid or vented fins on corners (Kwok and Bailey 1987), chamfering corners (Kawai 1998; Kwok et al. 1988), rounding corners (Carassale et al. 2014; Zhang and Samtaney 2016), recessing corners (He et al. 2014; Kurata et al. 2009; Tse et al. 2009), smart façade (Ding and Kareem 2020; Hu et al. 2017, 2019b) and fitting a splitter plate in the wake (Nakamura et al. 1991). Kwok and Bailey (1987) found that using solid and vented fins on the corners of a square tower has significant effects on both alongwind and crosswind responses. Fitting small solid fins and vented fins causes an increased in the alongwind response, while reduction in crosswind response occurred only for a limited range of reduced wind velocities. This study only tested the model configuration with fins at all four corners. The corner fins could be an option for reducing wind loading on bridge pylons as sketched in Fig. 1a if it is designed properly. A tall building with corner fins has been built in Dongguan, China, as shown in Fig. 1b.
On the other hand, recently substantial efforts have been made for enhancing windinduced vibrations of bluff bodies to improve the efficiency of wind energy harvesters via aerodynamic modifications (Hu et al. 2018, 2019a, c). For instance, two smalldiameter cylindrical rods were attached on two sides of a circular cylinder to successfully expand its aeroelastically unstable range to dramatically improve the efficiency of a vortexinduced vibrationbased wind energy harvester (Hu et al. 2016c). Song et al. (2017) placed a splitter plate in the lee of a circular cylinder and the splitter plate plays a similar role as the two cylindrical rods do in the study of Hu et al. (2016c). Similarly, a tail fin was fitted on the leeward face of a bluff body to improve the performance of a gallopingbased wind energy harvester by Noel et al. (2018). Another study to enhance the performance of the gallopingbased wind energy harvester is to fit solid fins to the leading corners of a square cylinder (Hu et al. 2016a), as shown in Fig. 2. In this study, results from wind tunnel experiments show that fitting fins on the two leading corners significantly enlarges the galloping response and hence improves the generated wind power by 150%. On the contrary, fitting fins on the two trailing edges suppresses the response, thereby reducing the output wind power. In addition, fitting fins on the four corners leads to a slight improvement on the performance of the harvester. Based on these observations, it is believed that fitting fins on corners of a square cylinder significantly influences aerodynamic characteristics of the square cylinder.
Although it has been recognized that fitting fins on the corners of a square cylinder has a remarkable effect on the cylinder’s aerodynamic characteristics, no study has yet been conducted to examine the effect of corner fins on aerodynamic forces and flow filed of the square cylinder systematically. This study aims to evaluate this effect and clarify the related mechanism via wind tunnel tests and large eddy simulation (LES). Three types of fin configurations, i.e. fitting fins to the leading corners, fitting fins to the trailing corners, and fitting fins to both leading and trailing corners were studied.
Experimental setup
Force measurement tests were performed on a square cylinder with or without corner fins in an opencircuit wind tunnel with a 500 mm (width) × 380 mm (height) test section as shown in Fig. 3a. The cylinder was mounted on a multiaxis load cell (JR3, INC) and spanned the wind tunnel horizontally. Three types of fin configurations, i.e. fitting fins only to the leading corners, fitting fins only to the trailing corners, and fitting fins to both leading and trailing corners, plus a plain cylinder without fins were tested as given in Fig. 4. The three types of fin configurations were simply termed leading fins, trailing fins, and four fins hereafter. The cylinder had a width of D = 50.8 mm; the fin length of D/6, which is the optimal fin length for enhancing performance of a square prismbased wind energy harvester (Hu et al. 2016a), was tested. The fins were fitted at the corners with an angle of 45° from the oncoming flow direction. The tests were performed at a wind speed of 8 m/s, which corresponds to a Reynolds number of 2.69 × 10^{4}. The oncoming flow with a turbulence intensity of 1.5% was imposed perpendicular to the windward face of the cylinder. The force measurements were taken at a sampling frequency of 400 Hz for a duration of 4000 vortexshedding cycles.
The blockage ratios for the plain cylinder case and the cylinder with corner fin cases are 13.3% and 16.5% respectively, which exceed the critical value of 5% for avoiding the blockage effect (Holmes 2015). Numerous studies have been conducted to evaluate the blockage effect and have proposed correction methods. For instance, Maskell (1965) developed a correction theory based on the concept of a quasisteady bubbleshaped wake. Modi and ElSherbiny (1973) observed that Maskell’s theory is valid for blockage ratios ranging from 5% to 10%. Thus, they developed a correction formula for cylinders and flat plates with blockage ratios larger than 10%. Raju and Singh (1975) suggested an empirical formula of the exponential form for twodimensional cylinders of rectangular section in a smooth flow with side ratio ranging from 0 to 2 and the blockage ratio ranged from 7.5% to 24%. All these studies were only concentrated on the correction of the steady force. Ota et al. (1994) proposed a correction formula for blockage effects on both steady and unsteady forces, e.g. mean drag coefficient, fluctuating drag coefficient and lift coefficient, and Strouhal number of twodimensional bluff bodies such as a square cylinder. According to comparisons with the previous experimental data, the Ota’s correction formula has been proved to be capable of estimating the wall effect quite accurately up to the blockage ratio of 20%. The Ota’s correction formula was, therefore, adopted to correct the blockage effect in the present study. The general correction formula is expressed as
where C_{F} represents the coefficient of F, ξ_{F} is the correction factor which has been provided by Ota et al. (1994), and the subscript ∞ denotes the value in an unbounded flow, h_{p} is the projected height of cylinder, h is the wind tunnel height and hence h_{p}/h is the blockage ratio for the present test configuration.
Numerical simulation configurations
Numerical methods
Threedimensional large eddy simulation (LES) turbulence model embedded in ANSYS FLUENT was used in the present study, since LES has been confirmed to accurately predict both mean and instantaneous flow fields around bluff bodies (Blocken 2014; Gousseau et al. 2013; Haque et al. 2014; Hu et al. 2015; Lam et al. 2012; Lam and Lin 2008; Li et al. 2013; Lim et al. 2009; Liu 2012; Tominaga et al. 2008; Yan and Li 2016; Zheng et al. 2012). Rodi (1997) compared LES and RANS model for flow around a square cylinder and a surfacemounted cube. He observed that RANS simulation severely underestimated the turbulence fluctuations while LES gave a significantly better prediction.
LES simulates large scale eddies by solving the filtered NavierStokes equations, in which the effect of small eddies is calculated using a subgrid scale (SGS) model. The present study chose the dynamic SmagorinskyLilly model as the SGS model. The flow is assumed to be Newtonian and incompressible. The filtered NavierStokes equations are given as
where i, j = 1, 2 and 3; u_{1}, u_{2} and u_{3} are the velocity components along x_{1} (i.e. longitudinal direction), x_{2} (lateral direction) and x_{3} (vertical direction) of the Cartesian coordinate system, respectively. The overbar denotes the filtering operator. ρ and v are air density and kinematic viscosity respectively. \( \overline{p} \) is the pressure and τ_{ij} is the components of the SGS stress tensor which is defined as
Based on the Boussinesq hypothesis, the subgridscale turbulent stresses are computed as
where \( {\overline{S}}_{ij} \) is the strain rate tensor for the resolved velocities and μ_{t} is the subgridscale turbulent viscosity. The SmagorinskyLilly model was adopted to calculate μ_{t} as:
where \( \left\overline{S}\right=\sqrt{2{\overline{S}}_{ij}{\overline{S}}_{ij}} \) is the characteristic filtered rate of strain and \( {L}_s=\min \left(\kappa d,{C}_s{V}_c^{1/3}\right) \) is the mixing length for the subgrid scales calculated according to κ the von Karman constant, d the distance to the closest wall, V_{c} the volume of the computational cell and C_{s} the Smagorinsky coefficient.
The finite volume method was adopted to solve the unsteady incompressible NavierStokes equation. The PISO scheme was used to solve the pressurevelocity coupling. The bounded second order implicit scheme was selected for time discretization; the second order scheme was used for spatial discretization of pressure; and the bounded central differencing was employed for spatial discretization of the momentum equations. For the unsteady simulation, time step is another important parameter. The time step (Δt) of 2 × 10^{− 5} s was selected after testing a few shorter and longer time steps, and it ensured the CourantFriedrichsLewy (CFL) number less than 1 in the computational domain. Each simulation was initialized with the solution of a preceding RANS simulation for fast convergence of computation. For all simulations, more than 1000 nondimensional time steps, corresponding to approximately 133 vortexshedding cycles that is much larger than the number of cycles adopted in the previous studies summarized by Rodi et al. (1997) and Voke (1997), were taken to assure reliable results.
Computational domain and mesh arrangement
The width (D) of the cross section was 24 mm, and the length of the square cylinder was 4D, which has been widely used in the literature (Nakayama and Vengadesan 2002; Rodi et al. 1997; Sohankar et al. 1999; Voke 1997). The distance between the windward face of the cylinder and the inlet was 8D. The lateral boundary was 5D away from the lateral face, which is identical to that adopted by Sakamoto et al. (1993) and larger than 4D used by Breuer et al. (2000). To allow flow redevelopment behind the wake region, the outlet boundary was set 17D away from the leeward face in terms of the previous studies (Rodi et al. 1997; Sohankar et al. 1999).
At the inlet boundary, a smooth flow with a wind speed of U = 12 m/s was imposed, leading to a Reynolds number of 1.90 × 10^{4}, which is lower than that in the wind tunnel tests. For the square prisms with or without corner fins, this type of bluff body with sharp edges is not sensitive to the Reynolds number (Holmes 2015). Therefore, the difference in the Reynolds number between wind tunnel tests and LES studies is believed to be unable to cause considerable discrepancy in the results of aerodynamic characteristics. The two lateral boundaries were defined as a symmetry boundary condition that was used to model zeroshear slip walls in viscous flows. A pair of translational periodic conditions were enforced on the top and bottom of the computational domain. A nonslip wall boundary condition was imposed on the surfaces of the cylinder. Zerogauge pressure was adopted at the outlet.
Hexahedral meshes were used for the whole computational domain as shown in Fig. 5. To consider the influence of grid resolution on the numerical simulation, three systematically and substantially refined grids (i.e., GS1, GS2 and GS3) for the plain square cylinder case were tested prior to launching the final numerical simulations. The specifications of the grids used are given in Table 1. Comparisons of mean pressure coefficients around the square cylinder between previous studies and the present numerical simulations are presented in Fig. 6; part of the numerical simulation results are compiled in Table 2 with data from previous studies. Evidently, the mean pressure coefficients on the four sides have good agreement between the grid schemes GS2 and GS3 and these coefficients are also consistent with the results in the previous studies (Bearman and Obasaju 1982; Cao and Tamura 2016; Otsuki et al. 1978). However, the simulation based on the GS1 scheme showed a worse prediction for the mean pressure coefficients on the leeward face.
The drag, lift coefficients and Strouhal number of the square cylinder obtained from the three grid schemes are compared with previous studies in Table 2. The mean drag coefficient and the Strouhal number are defined as
where F_{d} and F_{l} are the drag and lift forces of the cylinder respectively; f_{v} is the vortex shedding frequency; D is the width of the cross section and U is the oncoming flow velocity set at the inlet boundary condition. The comparisons with present experimental results and previous studies’ results show that GS2 and GS3 gave more accurate predictions on drag and lift coefficients than GS1. The improvement attributed to the increase in the grid cell from GS2 to GS3 is not very distinct. The grid scheme GS2 was, therefore, selected for the final computation to save computation time. It should be noted that although GS2 was a grid scheme for the plain cylinder, the same grid size distribution for the whole domain was also used for all other cylinders with fins in the present study.
Simulation cases
The simulation cases are identical with the cases tested in the wind tunnel. The grid information based on grid scheme GS2 for these cases is shown in Table 3. The existence of the fins reasonably increases the total number of grids. The mean y^{+} values for all cases approximately ranged from 0.32 to 0.4. Only a little proportion of y^{+} plus values were higher than 1, the suggested threshold for LES.
Results and analyses
Mean pressure coefficients
Mean pressure coefficients (\( \overline{Cp}=\left(p{p}_{\infty}\right)/\Big(1/2\rho {U}^2 \))) around the cylinder surface at midspan, i.e. z = 2D, for the four cases are compared in Fig. 7. In the windward face (AB), \( \overline{Cp} \) at the stagnation point, i.e. the middle of the windward side, is justifiably slightly lower than 1.0 for all four cases. From the stagnation point to the two edges, \( \overline{Cp} \) gradually decreases, especially for the cases without leading fins, i.e., the plain cylinder case and the trailing fin case. By contrast, the decrease in the cases with leading fins, i.e. the leading fin case and the four fin case, is much less remarkable. At points a and b, \( \overline{Cp} \) is still very large, and only slightly smaller than that at the stagnation point, while it is much larger than in the cases without leading fins. \( \overline{Cp} \) on the leading fins dramatically drops from the base to the tip, i.e. from a to A and from b to B.
For the two side faces (AD and BC), their pressure coefficients are negative due to flow separation, and the distributions on the two side faces are symmetrical in a sensible way. Overall, \( \overline{Cp} \) on the side faces of the trailing fin case has the largest value. The value of the plain cylinder is more negative than the trailing fin case. Therefore, the existence of trailing fins reduces the suction on the side face. On the contrary, the two cases with leading fins, i.e. the leading fin case and the four fin case, have much lower \( \overline{Cp} \) than the plain cylinder, which implies that the leading fins play a role to enhance the suction. Furthermore, the case with pure leading fins has more negative \( \overline{Cp} \) than the case with four fins, which further confirms the role of the trailing fins to reduce suction on the side face. Consequently, it is concluded that the leading fins enhance suction on the side face, whereas the trailing fins are able to reduce the suction over there.
For the leeward face (CD), the trailing fin case has much less suction, while the leading fin case exhibits significantly higher suction. Similar to the observations on the side face, it is believed that the trailing fins serve to weaken the suction on the leeward face, whereas the leading fins play a role to amplify the suction. Their effects on suction counteract each other in the four fin case, leading to suction that is generally consistent with the plain cylinder. For easy reference, the mean base pressure coefficients for the four cases are given in Table 4.
In summary, the leading fins enhance the suction on both side faces and leeward face, while the trailing fins play a role to weaken the suction on these faces. This interesting finding provides an effective aerodynamic strategy to control the surface pressure of square or rectangularsectioned bluff bodies, such as reduce the suction on side and leeward faces of tall buildings to safeguard the façade under strong wind.
Force coefficients and vortex shedding characteristics
Mean drag coefficients (\( \overline{C_d} \)), Strouhal numbers (S_{t}), and RMS lift coefficients (\( {C}_l^{RMS} \)) from LES and wind tunnel tests are compiled in Table 5; comparisons between these two sets of data are made. The differences of \( \overline{C_d} \) predicted by LES and wind tunnel tests (abbreviated to EXP) are within 6.3% for the four cases, which indicates that LES provides a pretty good prediction to the mean drag coefficients. Likewise, the differences of S_{t} from LES and wind tunnel tests are within 7.2% for all the cases except the leading fin cases, of which the difference is 12%. By contrast, the differences of \( {C}_l^{RMS} \) between the two sets of data are relatively larger and the maximum reaches 16% for the leading fin case. These relative large differences may be induced by the oncoming flow turbulence with a turbulence intensity of 1.5% in the wind tunnel tests. Overall, the LES provides decent predictions on the aerodynamic properties of the cylinders.
Differences of these parameters between the cases with fins and the plain cylinder are expressed in percentage of that of the plain cylinder in Fig. 8. The two cases with leading fins, i.e. the leading fin case and the four fin case, have much greater \( \overline{C_d} \) than the plain cylinder; the leading fins dramatically increase \( \overline{C_d} \) by approximately 50% and 30% in the two cases respectively. These findings can be verified by previous study. Kwok and Bailey (1987) reported that fitting fins to the four corners increased the drag force and mean alongwind response of a tall square tower compared with a plain square tower, which is consistent with the present results.
On the contrary, the trailing fins in the trailing fin case reduce \( \overline{C_d} \) by about 15%, which agrees with the observation of galloping response reduction resulting from fitting fins onto the two trailing corners of a square cylinder in Hu et al. (2016a). The increase by 30% in \( \overline{C_d} \) for the four fin case is considered a resultant effect of leading fins and trailing fins. Overall, the leading fins can increase mean drag substantially, while the trailing fins reduce mean drag.
Similar to their respective changes in \( \overline{C_d} \), the leading fin case has a much larger \( {C}_l^{RMS} \) with an increase of approximately 70%, and the four fin case has an increase of about 45%. However, the trailing fin case has a reduction of about 36%. Therefore, it is believed that the leading fins increase the RMS lift coefficient while the trailing fins decrease the coefficient, and both changes are remarkable.
Power spectra of the lift forces obtained by LES are given in Fig. 9 and the spectra reflect the interaction intensity of the shear layer with the side face. The spectrum of the plain cylinder agrees well with that in Murakami et al. (1999) within the concerned frequency range. The Strouhal numbers (S_{t}) listed in Table 5 are extracted from these spectra. All three types of fin configurations reduce S_{t}, which implies that the fins slow down the vortex shedding process. Specifically, the Strouhal number for the trailing fin case is slightly lower than that of the plain cylinder, as shown in Fig. 8. However, the spectrum energy, represented by the peak values in Fig. 9, is obviously lower than of the plain cylinder. By contrast, both the leading fin case and the four fin case have a much smaller Strouhal number, approximately 20% lower than that of the plain cylinder, whereas the spectrum energy is higher than that of the plain cylinder. This observation is consistent with the finding reported by Kwok and Bailey (1987). In their study, a comparison of the lift force spectrum between the plain square tower and the square tower with four fins was made. The comparison also shows that the square tower with four fins exhibits a lower S_{t} but higher spectrum energy, which further verifies the reliability of the current LES study. In addition, in Fig. 9, the spectrum energy of the leading fin case is obviously larger than that of the four fin case. Apparently, the leading fins lead to a lower frequency but higher spectrum energy, while the trailing fins result in a slightly lower frequency and lower energy.
Flow pattern around the cylinders
The considerable effects of corner fins on the aerodynamic characteristics of a square cylinder have been detailed above. The variations in the aerodynamic characteristics are associated with alterations in flow pattern around the cylinder. The flow patterns are discussed in this section to clarify the related mechanism.
Plain cylinder
Timeaveraged streamlines around the cylinder are given in Fig. 10. For the plain cylinder, the flow begins to separate at the two sharp leading corners and forms two recirculation zones beside the two side faces. A pair of recirculation zones are also identified in the near wake. The pressure inside each recirculation zone is negative as shown in Fig. 11 and it therefore leads to negative pressures on both the side faces and the leeward face (see Fig. 7).
Leading fin case
The magnitude of the negative pressure on the side and leeward faces is highly dependent on the shape and dimension of the recirculation zones (Bearman and Trueman 1972; Hu et al. 2016b; Huot et al. 1986; Tombazis and Bearman 1997; Kurata et al. 2009). Compared to the flow pattern beside the side face of the plain cylinder, the recirculation zone for the leading fin case is more complicated. The zone consists of three recirculation bubbles, one dominant big bubble and two concomitant small bubbles. The dominant bubble is larger than the bubble beside the side face of the plain cylinder and its location is further from the side face. As a result, the curvature of the separated shear layer is greater than that of the plain cylinder, which can also be observed clearly in the instantaneous spanwise vorticity pattern in Fig. 12. In Fig. 12b, the shear layer separated from the leading fins and has an obvious reattachment/interaction with the side face, which leads to a large curvature of the shear layer. As stated by Laneville et al. (1975), the suction depends on the curvature of the shear layer; the stronger the curvature, the larger the suction. Therefore, the larger curvature of the shear layer for the leading fin case leads to the larger suction on the side face than that for the plain cylinder as shown in Figs. 7 and 11.
The dimension of the wake recirculation zone, i.e. width and length, is directly related to the base pressure behind a twodimensional bluff body (Bearman 1965, 1967; Tombazis and Bearman 1997). Moreover, the base pressure is inversely associated with the drag of a bluff body (Bearman and Trueman 1972). The drag coefficient is proportional to the wake width, while inversely proportional to the length of the recirculation zone, i.e. the vortex formation length (He et al. 2014; Hu et al. 2016a, b; Tamura and Miyagi 1999; Ueda et al. 2009). Meanwhile, the fluctuating lift coefficient is also inversely proportional to the length of the recirculation zone (Lam and Lin 2008). Because a longer recirculation zone in the wake indicates that the rollup of shear layer in the wake is farther from the buff body, hence the effect of the shear layer rollup on the side face is weaker, which leads to a lower fluctuating lift coefficient. Although the difference in the vortex formation length between the plain cylinder case and the leading fin case is tiny (approximately 11%), as shown in Fig. 10, the wake width of the leading fin case is clearly larger than that of the plain cylinder case. The larger wake width, actually a stronger curvature of the shear layer in the wake (see Fig. 12b), leads to a lower base pressure as shown in Fig. 11 and Table 4. Meanwhile, the pressure on the windward face of the leading fin case is larger as demonstrated in Fig. 7. Therefore, the much larger drag coefficient in the leading fin case than the plain cylinder case is a result of the lower base pressure and the larger pressure on the windward face.
The normalized instantaneous spanwise vorticity distributions at four instants during one period are given in Fig. 12. For the leading fin case, the separated shear layer has a stronger interaction with the side faces compared to the plain cylinder case. The curvature of the shear layer is remarkably larger, which is consistent with the observations in Fig. 10. The much stronger interaction results in the larger fluctuating lift coefficients on the side face as given in Fig. 8 and Table 5. Furthermore, the stronger interaction implies a more intense interruption in the vortex shedding process and hence a lower Strouhal number. Meanwhile, the stronger interaction leads to a higher energy in the lift force spectrum in Fig. 9.
Trailing fin case
As shown in Fig. 10, the streamline passing through the cylinder with trailing fins is quite different from that of other cases. The flow begins to separate at the leading corners, forms a recirculation zone beside the side face, then goes over the trailing fin and forms a very large recirculation zone in the wake. The shear layer is slightly less curved than that of the plain cylinder (also can be seen in Fig. 12) because the trailing fins push it away from the cylinder. The slightly less curved shear layers lead to slightly less negative pressures on/beside the side faces and the leeward face as given in Figs. 7 and 11. The less negative pressures on the leeward face along with the generally consistent pressure distribution on the windward face leads to a 15% decrease in drag coefficient as presented in Fig. 8. Referring to the recirculation zone dimension, the lower drag coefficient for the trailing fin case can also be inferred. Apparently, the wake recirculation zone is dramatically elongated by the trailing fins (see Fig. 10). As mentioned above, the drag coefficient is inversely proportional to the length of the wake recirculation zone. Therefore, the longer recirculation zone results in a lower drag coefficient. The less fluctuating lift coefficient can also be attributed to the elongated wake recirculation zone. The spanwise vorticity distributions in four instants shown in Fig. 12c indicate that the trailing fins push the separated shear layer away and weakens its interaction with the side faces. The weaker interaction causes a lower spectrum peak in the lift force spectrum.
Four fin case
Compared with the cylinder with only leading fins in Figs. 10 and 12, the shear layer for the cylinder with four fins is less curved due to the presence of the two trailing fins. Therefore, the pressures on/beside the side faces and the leeward face are less negative than those for the cylinder with only leading fins. However, the pressures are still lower than those for the plain cylinder. As a result, the drag coefficient is lower than that of the leading fin case but higher than that of the plain cylinder. The rollup of the shear layer occurring in the near wake is closer to the leeward face of the cylinder compared with the plain cylinder case as shown in Fig. 12, which induces a larger fluctuating lift force in the four fin case.
Discussions
The above sections have demonstrated that the fins fitted at corners of square cylinder have a remarkable influence on the aerodynamic properties including surface pressure, drag force, lift force, vortex shedding strength and frequency of the cylinder. The trailing fins suppress suctions on side faces and leeward face, and also reduce not only drag force but also fluctuating lift force. As a result, the trailing fin configuration is desirable for the windresistant design of bridge pylons and tall buildings. However, the natural wind direction is variable. If two fins are fixed at two edges of bridge pylons and tall buildings, there are three possible scenarios due to change in wind direction: the leading fin configuration, the trailing fin configuration, one fin at leading edge and the other one at trailing edge. Therefore, fixing two fins at two edges of bridge pylons and tall buildings is very impractical. Nevertheless, smart controlling the position of the fins in terms of wind direction by using the cutting edge artificial intelligence techniques (Bao and Li 2020; Hu et al. 2020; Hu and Kwok 2020; Jin et al. 2018; Li et al. 2018), more specifically reinforcement learning techniques (Fan et al. 2020; Rabault et al. 2019), provides a possibility to take advantage of the merits of the trailing fin configuration. In detail, the fins are installed inside tall buildings at four corners but can be protruded from the building, as shown in Fig. 13a. According to the wind direction, which can be monitored by using an anemometer at the building top, the fins at the two trailing edges are protruded from the building, while the other two fins are kept inside the building, which forms the trailing fin configuration. Another potential application of the trailing fin configuration is to reduce the hydrodynamic drag of bridge pier in a river. Compared to the application to reducing windinduced force acting on bridge pylons and tall buildings, this application is more straightforward because the flow direction in a river is fixed, as shown in Fig. 13b.
On the other hand, in practical applications, such as bridge towers and highrise buildings, the vortexinduced vibration (VIV) has threedimensional characteristics, and the VIV along the spanwise direction is not completely synchronous (Ricciardelli 2010; Li et al. 2015, 2016). In particular for a slender structure, the spanwise distribution of aerodynamic load on it is very important. If it is not fully understood, the prediction of overall aerodynamic force will be affected. Therefore, it is necessary to further study the spanwise correlation analysis and surface fluctuating wind pressure distribution of square column with fins, and verify the results of flow field simulation through PIV wind tunnel test.
Conclusions
This study has systematically evaluated the effect of corner fins on the aerodynamic characteristics of a square cylinder via wind tunnel tests and large eddy simulations. Three types of corner fin configurations, i.e. fitting fins only at the leading corners, fitting fins only at the trailing corners, and fitting fins at both leading and trailing corners were studied. The findings are summarized below, which have practical significances for both reducing flowinduced vibration of civil structures including bridge pylons and tall buildings, and enhancing flowinduced vibration for harvesting energy.
The corner fins exhibit a remarkable influence on the surface pressure of the square cylinder and hence its aerodynamic force. Specifically, the leading fins enhance the suction on both side faces and leeward face, while the trailing fins weaken the suction on these faces. This interesting finding provides an effective aerodynamic strategy to control the cladding pressure of tall buildings or other squaresectioned bluff bodies. Meanwhile, the leading fins increase mean drag substantially while the trailing fins reduce the mean drag less significantly. The four fin case exhibits a resultant effect of leading fins and trailing fins, and it has a larger mean drag than the plain cylinder and a lower mean drag than the leading fin case. Similar to the effects of the fins on the mean drag, the leading fins increase the RMS lift coefficient significantly, whereas the trailing fins decrease the coefficient remarkably. In addition, the leading fins lead to an obviously lower vortex shedding frequency but much higher energy in the lift force spectrum, while the trailing fins result in a slightly lower frequency but much lower spectrum energy.
For the leading fin case, the larger curvature of the shear layer leads to larger suctions on both the side face and the leeward face than those of the plain cylinder, and hence a larger mean drag coefficient. Meanwhile, the separated shear layer has a stronger interaction with the side faces, which causes a larger fluctuating lift coefficient and a higher spectrum energy in the lift force spectrum.
For the trailing fin case, the recirculation zone is much longer than that of the plain cylinder and the shear layer is much less curved. The much less curved shear layer leads to less suctions on/beside the side faces and the leeward face, and hence a lower mean drag coefficient. The less fluctuating lift coefficient can also be attributed to the elongated wake recirculation zone. The trailing fins push the separated shear layer away and weakens its interaction with the side faces. The weaker interaction causes a lower spectrum peak in the lift force spectrum. The four fin case is believed to be a resultant of the leading fin case and the trailing fin case.
Although this study has systematically investigated the effect of corner fins on the aerodynamic characteristics of a square cylinder via both wind tunnel tests and large eddy simulations, it is worth devoting more efforts on this topic to further understand the effects due to its practical significance. For example, to understand the fluidstructure interaction behavior of a square cylinder with corner fins, it is suggested to perform aeroelastic tests in a wind tunnel or conduct numerical simulations with moving mesh. On the other hand, advanced experimental techniques, e.g. particle image velocimetry, can be used to visualize the flow field around a square cylinder with corner fins.
Availability of data and materials
No objection for data sharing.
Abbreviations
 LES:

Large eddy simulations
 RANS:

Reynoldsaveraged Navier–Stokes
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Acknowledgements
The authors gratefully acknowledge the supports from National Key R&D Program of China (2019YFC0810702) and Shenzhen Basic Research Program (JCYJ20170811160652645).
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National Key R&D Program of China (2019YFC0810702) and Shenzhen Basic Research Program (JCYJ20170811160652645).
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Qiulei Wang: Formal analysis, Investigation, Validation, Writing  original draft and review & editing. Qi Jiang: Formal analysis, Methodology, Validation, Writing  original draft. Gang Hu: Conceptualization, Methodology, Investigation, Formal analysis, Writing  original draft. Xiao Chen: Investigation, Writing  original draft. Chao Li: Methodology, Writing  review & editing, funding secure. Yiqing Xiao: Conceptualization, Methodology, Supervision, funding secure, Writing  review & editing. The author(s) read and approved the final manuscript.
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Wang, Q., Jiang, Q., Hu, G. et al. Aerodynamic characteristics of a square cylinder with corner fins. ABEN 2, 20 (2021). https://doi.org/10.1186/s4325102100042x
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Keywords
 Large eddy simulation
 Square cylinder
 Aerodynamic treatment
 Corner modification
 Corner fins