3.1. Drag and lift coefficients

Figure 3 plots, for a number of studies, the relationship of both the mean drag coefficient, $C_D$, and the fluctuating lift coefficient, $\sigma _{C_L}$, with Reynolds number. For clarity, the results of only the smoothest and the roughest cylinder in the current study are given in this figure. Figure 3(a) includes $C_D$ measurements from the sectional pressure measurements of van Hinsberg (Reference van Hinsberg2015) while those obtained from their force measurements are excluded. Within the postcritical regime, the degree of agreement in $C_D$ amongst the works is high, and perhaps surprising given the differences in the aspect and blockage ratios of their set-ups (see table 1). A reduction in aspect ratio is expected to decrease drag since the fluid feeding from the edge of the cylinder increases the base pressure (Basu Reference Basu1985). Considering the large difference in the blockage ratios amongst the different set-ups (from 5 % to 18 %); this agreement is indicative that blockage corrections work well for the predictions of $C_D$.

Figure 3.

A comparison of (a) the mean drag coefficient and (b) the fluctuating lift coefficient in this study with earlier works. Confidence intervals were calculated as described in § 2.2: ${\cdot }\ {\cdot }\ \triangleleft\ {\cdot }\ {\cdot }$ Achenbach (Reference Achenbach1971), $k_s/D = 1.1 \times 10^{-3}$; ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ van Hinsberg (Reference van Hinsberg2015), $k_s/D = 1.2 \times 10^{-3}$; ${\cdot }\ {\cdot }\ {\triangleright }\ {\cdot }\ {\cdot }$ Güven et al. (Reference Güven, Farell and Patel1980), $k_s/D = 3.11 \times 10^{-3}$; ${\cdot }\ {\cdot }\ {\square }\ {\cdot }\ {\cdot }$ Eaddy (Reference Eaddy2019), $k_s/D = 1.2 \times 10^{-3}$, $k/D=0.8 \times 10^{-3}$, aspect ratio 9; ${\cdot }\ {\cdot }\ {\blacksquare }\ {\cdot }\ {\cdot }$ Eaddy (Reference Eaddy2019), $k_s/D = 1.2 \times 10^{-3}$, $k/D=0.8 \times 10^{-3}$, aspect ratio 5.7; ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown) current, $k_s/D = 1.1 \times 10^{-3}$; ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red) current, $k_s/D = 3 \times 10^{-3}$.

Figure 3(b) gives the variation of the fluctuating coefficient of lift with Reynolds number. The scatter in measurements of $\sigma _{C_L}$ across different investigations is comparatively larger than that of $C_D$ owing to its higher sensitivity to aspect ratio, blockage ratio, mode of generation of roughness and method of measurement (Norberg Reference Norberg2003). In particular, the influence of aspect ratio and blockage is also evident in the difference in $\sigma _{C_L}$ obtained from two different set-ups of the same roughness in Eaddy (Reference Eaddy2019). While their larger aspect ratio ($AR =9$) results for similar roughness agree well with the current study, $\sigma _{C_L}$ values from the smaller aspect ratio ($AR = 5.7$) are considerably higher.

On the other hand, $\sigma _{C_L}$ reported in van Hinsberg (Reference van Hinsberg2015) is much lower than that for the current study at the same Reynolds number ($\sim$0.1 compared with $\sim$0.25) despite both set-ups having similar aspect ratio and relative roughness. A possible cause of this discrepancy is the method of generating and representing roughness. While van Hinsberg (Reference van Hinsberg2015) used plasmatic metal coating to generate surface roughness, the current work uses sandpaper. The roughness of a sandpaper is expected to be more randomly distributed than that obtained from machining the surface. The agreement in the mean $C_D$ indicates that the influence of the roughness on the broad flow features is similar in the two investigations. The relatively large disagreement in $\sigma _{C_L}$ could, in part, be due to the distribution of roughness and the resulting variation across different methods of generation.

In addition to the mode of roughness generation, the technique used for determining $\sigma _{C_L}$ in the two studies is also different. van Hinsberg (Reference van Hinsberg2015) measured the instantaneous forces on the entire cylinder using a force balance to determine the fluctuating lift coefficient. In contrast, for the current study, the time-varying lift coefficient and its standard deviation are obtained through the integration of instantaneous pressure coefficients at a single cross section of the cylinder. This suggests that the spanwise correlation of fluctuating force components plays an important role; this will be examined in more detail in § 3.5. Moreover, preliminary experiments during the initial phase of the current study revealed high sensitivity of $\sigma _{C_L}$ to the presence of a gap between the cylinder and wind-tunnel walls that is required in order to measure forces using external balances. Kacker, Pennington & Hill (Reference Kacker, Pennington and Hill1974) reported that an airgap between the active and dummy cylinder as small as $0.1$ mm could result in lift force measurements 5–10 times smaller than the actual value. Jones, Cincotta & Walker (Reference Jones, Cincotta and Walker1969) also found that gaps of $0.7$ mm could have significant effects on the flow configuration over a smooth cylinder. More information about the influence of this gap and differences between lift coefficients measured through total force and cross-sectional pressure methods for smooth cylinders is given in Norberg (Reference Norberg2003).

Limited and widely varying data amongst different studies and increased sensitivity of the lift to the parameters of flow set-up makes comparisons of $\sigma _{C_L}$ for rough cylinders particularly difficult. Scarcity of information about $\sigma _{C_L}$ for different roughnesses in the postcritical regime was a major motivation behind this work and the results presented here aim to address this knowledge gap.

Figure 4 gives the variation of the mean coefficient of drag and the fluctuating lift coefficient with Reynolds number for different roughnesses. Flow parameters in the critical/supercritical regime where the cylinder flow experiences combinations of laminar separation, transition to turbulence in the shear layer, turbulent reattachment, intermittent turbulent separation and asymmetric shedding are very sensitive to disturbances in the flow and, hence, the confidence intervals are larger. This region of high sensitivity extends up to $Re\sim 2.3\times 10^5$ for the smoothest roughness tested and up to $Re\sim 1\times 10^5$ for the roughest tested in the current work. Owing to the higher sensitivity of the lift to the pressure distribution near separation, these confidence intervals for the measurements of $\sigma _{C_L}$ are larger than those of $C_D$. Tests for the same roughness and similar $Re$ are found to intermittently contain the LSB for different proportions of time resulting in a wide range of $\sigma _{C_L}$, thus making it difficult to infer representative trends through the critical regime. The reader is referred to Cadot et al. (Reference Cadot, Desai, Mittal, Saxena and Chandra2015) for more information regarding the flow configuration and the stability of LSB through the critical regime. Note that § 3.4 explores the intermittency of the LSB and the influence of roughness in further detail. Repeatability is improved beyond the critical regime and the observed variations with Reynolds number are relatively smooth.

Figure 4.

(a) Mean coefficient of drag, $C_D$, and (b) fluctuating coefficient of lift, $\sigma _{C_L}$ for different roughness. Confidence intervals were calculated as described in § 2.2: ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red), $k_s/D=3\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacktriangle }\ {\cdot }\ {\cdot }$ (green), $k_s/D=1.9\times 10^{-3}$; ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ (blue), $k_s/D=1.4\times 10^{-3}$; and ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown), $k_s/D= 1.1\times 10^{-3}$.

An increase in roughness leads to a reduction in the critical Reynolds number, the Reynolds number at which $C_D$ is minimum. Roughness particles promote the transition to turbulence near the surface of the cylinder and, hence, an increase in roughness leads to an earlier transition in the boundary layer, i.e. transition to turbulence immediately after separation, and the LSB occurs at a lower Reynolds number for larger roughness. From the current tests, the critical Reynolds number of the roughest surface tested ($k_s/D=3\times 10^{-3}$) is ${\sim }1\times 10^5$ while that of the smoothest surface tested ($k_s/D=1.1\times 10^{-3}$) is ${\sim }2\times 10^5$. Beyond the critical Reynolds number, the flow configuration changes from stable reattachment of the separation bubble on both sides of the cylinder to asymmetric reattachment and eventually to no reattachment on the two sides of the cylinder (Cadot et al. Reference Cadot, Desai, Mittal, Saxena and Chandra2015). This results in an increase in $C_D$ increase as Reynolds number increases in the supercritical regime. Increasing roughness causes the LSB to become more unstable, thereby leading to a lower range of $Re$ where an intermittent LSB occurs and, hence, a smaller supercritical regime. By destabilising the LSB, roughness promotes coherent vortex shedding over the span of the cylinder and, hence, increases the forces on the overall span of the cylinder since the flow separates earlier when the LSB is absent.

At postcritical Reynolds numbers, the boundary layer in the adverse pressure gradient region is turbulent and hence, separates later than the laminar boundary layer of subcritical regime. Due to this delayed separation, the postcritical $C_D$ is lower than that of the subcritical $C_D$ for a given roughness. On the other hand, an increase in surface roughness causes an earlier separation of turbulent boundary layers in adverse pressure gradients due to an increased momentum deficit near the wall (Song & Eaton Reference Song and Eaton2002; Aubertine, Eaton & Song Reference Aubertine, Eaton and Song2004). Thus, at a fixed postcritical $Re$, $C_D$ increases with an increase in roughness. The mean coefficients of drag $C_D$ are found to be $\sim$0.87 and $\sim$1.01, respectively, for the smoothest and roughest cylinders at the highest Reynolds number of the current tests ($6.8 \times 10^5$).

Similar to $C_D$, the postcritical $\sigma _{C_L}$ increases with increasing roughness. Power spectra of the velocity fluctuations given in figure 16 reveal an increased energy content at the shedding frequency for increased roughness. This indicates that an increase in roughness results in larger fluctuations and hence a larger $\sigma _{C_L}$. At $Re\sim 6.7\times 10^5$, $\sigma _{C_L}$ is $0.28$ and $0.34$, respectively, for the smoothest and roughest cylinder tested.

3.2. Circumferential pressure distributions

Mean and standard deviation circumferential pressure distributions presented in this study are the average of distributions over the four spanwise locations. To better highlight variations, these spanwise averages are presented only for half of each circumference. These half-circumference pressure distributions are the average of the upper and lower halves of the cylinder. Across all the postcritical Reynolds numbers ($Re\geq 3\times 10^5$) and roughnesses tested, the maximum deviation, $|\overline {C_P}(\theta )-\overline {C_P}(360-\theta )|$ is $0.1$ and this is seen in the large gradient region of $0^{\circ }\leq \theta \leq 90^{\circ }$. Over $100^{\circ }\leq \theta \leq 180^{\circ }$, this maximum reduces to ${<}0.01$. The mean deviation across all the tests is less than $0.08$ for $0^{\circ }\leq \theta \leq 180$.

Figure 5 gives the circumferential mean pressure coefficient of cylinders of different roughnesses at postcritical Reynolds numbers. For a given roughness, the coefficient of pressure over the upstream region of the cylinder (${\sim }(300^{\circ }$–$0^{\circ }$–$60^{\circ })$) does not exhibit any noticeable change with Reynolds number, generally following the potential flow solution. The observable changes with increasing Reynolds number are a decrease in the coefficient of pressure in the downstream/base region (${\sim }(100^{\circ }$–$180^{\circ }$–$260^{\circ })$), and an increase in the coefficient of pressure in the acceleration region (${\sim }(75^{\circ }$–$90^{\circ })$).

Figure 5.

Circumferential distributions of mean coefficient of pressure: $\star$, $k_s/D=3\times 10^{-3}$; $\triangle$, $k_s/D=1.9\times 10^{-3}$; $\bigcirc$, $k_s/D=1.4\times 10^{-3}$; $\lozenge$, $k_s/D=1.1\times 10^{-3}$; red solid line, $Re\sim 3\times 10^5$; green solid line, $Re\sim 4\times 10^5$; blue solid line, $Re\sim 5\times 10^5$; and brown solid line, $Re\sim 6.7\times 10^5$. (a) Effect of Reynolds number for different roughness. (b) Effect of roughness for different Reynolds number. Note that successive families of curves have been offset in the pressure coefficient by $-0.5$.

To examine these changes in further detail, three additional variables are introduced. Base pressure, $C_{P_b}$, is the mean coefficient of pressure over the downstream side of the cylinder. Minimum pressure, $C_{P_m}$, is the minimum coefficient of pressure on the cross-sectional surface. Wake angle, $\theta _w$, is the angle at which a linear regression fit of the coefficient of pressure profile from $C_{P_m}$ to $C_{P_b}$ intersects $C_{P_b}$. Both $C_{P_m}$ and $\theta _w$ given are the mean of the values found on each half of the cylinder. Furthermore, all three variables presented are the corresponding spanwise averages over a sample of four cross sections. The definitions of these variables for a representative $C_P$ distribution are given in the figure 6(a).

Figure 6.

(a) Parameters of coefficient of pressure, (b) variation of wake angle, (c) variation of coefficient of minimum pressure, (d) variation of coefficient of base pressure, (e) pressure rise to separation with Reynolds number and (f) base pressure vs separation angle. Confidence intervals were calculated as described in § 2.2 Current: ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red) $k_s/D=3\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacktriangle }\ {\cdot }\ {\cdot }$ (green) $k_s/D=1.9\times 10^{-3}$, ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ (blue) $k_s/D=1.4\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown) $k_s/D=1.1\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\bigcirc }\ {\cdot }\ {\cdot }$ van Hinsberg (Reference van Hinsberg2015) $k_s/D = 1.2 \times 10^{-3}$; ${\cdot }\ {\cdot }\ {\triangleleft }\ {\cdot }\ {\cdot }$ Achenbach (Reference Achenbach1971), $k_s/D = 1.1 \times 10^{-3}$; ${\cdot }\ {\cdot }\ {\triangleright }\ {\cdot }\ {\cdot }$ Güven et al. (Reference Güven, Farell and Patel1980), $k_s/D = 3.11 \times 10^{-3}$, ${\cdot }\ {\cdot }\ {\square }\ {\cdot }\ {\cdot }$ Güven et al. (Reference Güven, Farell and Patel1980), $k_s/D = 2.5 \times 10^{-3}$.

While $C_{P_b}$ forms the prominent contribution to the coefficient of drag, $C_{P_m}$ is indicative of the degree of deceleration of flow velocity near the surface of the cylinder, i.e. the lower the $C_{P_m}$ the higher the velocity outside the boundary layer. In addition, $\theta _w$ is a nominal estimate of the separation angle obtained from the circumferential mean $C_P$ distribution. This estimate is smaller than the actual separation angle given by $\theta _s$ by ${\sim }5^{\circ }$ (Güven et al. Reference Güven, Farell and Patel1980); indeed, this correlates well with the $\theta _s$ measurements of Achenbach (Reference Achenbach1971) as seen in figure 6(b).

On the surface of a smooth cylinder, the laminar boundary layer in the subcritical flow separates earliest, near ${\sim }80^{\circ }$ on a smooth cylinder, followed by a turbulent boundary layer, between ${\sim }100\unicode{x2013}110^{\circ }$ on a smooth cylinder and a boundary layer with a LSB in the critical regime separates more downstream, between ${\sim }120^{\circ }\unicode{x2013}140^{\circ }$ on a smooth cylinder than the latter (Basu Reference Basu1985). A similar trend is observed in the measurements of $\theta _w$ against Reynolds number from the current results. At subcritical Reynolds numbers, $\theta _w$ is ${\sim }75^{\circ }$ for all the roughnesses tested and an increase in Reynolds number results in an increasing $\theta _w$ until it reaches a maximum (${\sim }108^{\circ }$ and ${\sim }125^{\circ }$ for the roughest and the smoothest cylinder, respectively). A further increase leads to a decrease in the wake angle and at large postcritical Reynolds numbers the wake angle approaches an asymptotic value of ${\sim }95^{\circ }$. This indicates that the separation angle also reaches an asymptotic value of ${\sim }100^{\circ }$ in agreement with Achenbach (Reference Achenbach1971).

Similar to the wake angle, the base pressure coefficient increases and then decreases with increasing Reynolds number. The peak in the base pressure occurs in the critical regime and coincides with the peak in the separation angle and also the minimum drag coefficient. As the Reynolds number is increased further, the change in base pressure decreases until eventually approaching an asymptotic value of ${\sim }-0.95$. The convergence of $C_{P_b}$ with roughness at large Reynolds numbers is slightly wider than that of $\theta _w$. Changes in the minimum pressure, $C_{P_m}$ are in the opposite direction, i.e. an increase in Reynolds number causes a decrease and then an increase in $C_{P_m}$, before eventually approaching an asymptotic value. Unlike $\theta _w$ and $C_{P_b}$, the asymptotic value in the minimum pressure at the highest Reynolds numbers tested is a function of roughness, with larger roughness leading to a higher $C_{P_m}$, i.e. larger deceleration of the flow.

For the smoothest cylinder tested ($k_s/D=1.1\times 10^{-3}$), the changes in $\theta _w$, $C_{P_b}$ and $C_{P_m}$ when the Reynolds number is increased from $Re\sim 4\times 10^5$ to $Re\sim 6\times 10^5$ are approximately $4\,\%$, $6\,\%$ and $5\,\%$, respectively. The corresponding changes for the roughest cylinder tested ($k_s/D=3\times 10^{-3}$) are $1\,\%$, $3\,\%$ and $2\,\%$, respectively. At the largest Reynolds number tested ($Re\sim 6\times 10^5$), the changes in these quantities, ($\theta _w$, $C_{P_b}$ and $C_{P_m}$) from the smoothest cylinder to the roughest cylinder tested are $3\,\%$, $5\,\%$ and $14\,\%$, respectively. These observations indicate that while the flow near and beyond separation becomes nearly independent of roughness at large Reynolds numbers, flow in the deceleration region and particularly near the minimum pressure is still dependent on the degree of surface roughness, even though it is relatively independent of the Reynolds number.

Amongst different investigations, the degree of scatter in the pressure rise to separation $C_{P_b}-C_{P_m}$ is slightly larger than that in $C_D$ and $C_{P_b}$ (note the different $y$-scales in figure 6c,e). This is in contrast to the proposal of Güven et al. (Reference Güven, Farell and Patel1980) and Farell et al. (Reference Farell, Carrasquel, Güven and Patel1977) that the pressure rise to separation is less sensitive to the effects of aspect ratio and blockage than $C_{P_b}$ and $C_{P_m}$. The present rough cylinder data show that the base pressure results among different studies have a smaller scatter followed by the minimum pressure. The deviation in the pressure rise to separation is a consequence of that in minimum pressure. In this regard, the use of spanwise variation of minimum pressure to ascertain the effects of blockage and aspect ratio in the postcritical region is recommended over the base pressure distribution that has been used before (Stansby Reference Stansby1974; Fox & West Reference Fox and West1990).

Blockage corrections to pressure distributions (Allen & Vincenti Reference Allen and Vincenti1944; Roshko Reference Roshko1961) do not include the effect of wake blockage on pressure gradients (Farell et al. Reference Farell, Carrasquel, Güven and Patel1977) and is a possible cause of the larger scatter in the pressure distribution parameters from different studies when compared with that of $C_D$. Another limitation in the application of blockage corrections is that the corrected $C_P$ distributions do not directly correspond to the corrected $C_D$ values since the corrections are independent. In this context, one should exercise care in applying the corrections to predict the pressure distributions free of wind-tunnel influences, since an agreement in the blockage corrected $C_D$ does not imply agreement in the blockage corrected $C_P$. Moreover, corrections to $\sigma _{C_L}$ are unavailable since the influence of blockage on the fluctuating parameters is still uncertain. This emphasises the importance of data obtained from a high-aspect-ratio and low-blockage set-up similar to that used in the current work.

Since wake angle and base pressure appear to be in good correlation, the coefficient of base pressure, $C_{P_b}$, is plotted against the wake angle $\theta _w$ in the postcritical regime ($Re\geq 3\times 10^5$) in figure 6(f). The data plotted are obtained from tests of different roughnesses, i.e. different minimum pressure (see figure 6c) and, thus, a different pressure distribution before separation. Hence, a good correlation across different roughnesses indicates that the base pressure is a strong function of the separation angle and only a weak function of the flow before separation in the postcritical regime. From figure 6(b), in postcritical flows, an increase in roughness at a constant Reynolds number or an increase in Reynolds number for a fixed roughness lead to a decrease in the separation angle. Figure 6(f) indicates that the change in base pressure coefficient arising due to a change in the separation angle is similar for all roughnesses tested. Since the base pressure coefficient forms the major contribution to the coefficient of drag, this results in the drag coefficient being similar in postcritical flows regardless of whether the separation angle is a result of increasing roughness or increasing Reynolds number. This forms the basis for collapse of $C_D$ when plotted against roughness Reynolds number, $Re_{k_s}$, and this is further discussed in § 3.7.

3.3. Fluctuating pressure coefficient

Figure 7 gives the distribution of the fluctuating pressure coefficient on the cylinder surface at different Reynolds numbers and roughnesses. The two significant trends with increasing Reynolds number post the critical regime are an increase in $\sigma _{C_P}$ over the circumference (more evident in the downstream region); and an upstream movement of the angle at which $\sigma _{C_P}$ is maximum. A peak in $\sigma _{C_P}$ is an indication of boundary-layer separation in the vicinity and since separation moves upstream with increasing Reynolds number, the location of maximum $\sigma _{C_P}$ also moves upstream. The smaller local maximum near ${\sim }160^{\circ }$ might indicate shear-layer roll up closer to the surface of the cylinder near that region. This smaller peak is less significant at lower Reynolds numbers (near $Re\sim 3\times 10^5$) especially for the smoother cylinders due to weaker vortex shedding at those Reynolds numbers. For a given roughness, an increase in velocity leads to an increase in the turbulent kinetic energy near the surface, causing an overall increase of $\sigma _{C_P}$ as the Reynolds number is increased. Moreover, earlier separation is also expected to cause larger fluctuations in the downstream region of the cylinder.

Figure 7.

Circumferential distributions of the fluctuating coefficient of pressure: $\star$, $k_s/D=3\times 10^{-3}$; $\triangle$, $k_s/D=1.9\times 10^{-3}$; $\bigcirc$, $k_s/D=1.4\times 10^{-3}$; $\lozenge$, $k_s/D=1.1\times 10^{-3}$; red solid line, ${\sim }3\times 10^5$; green solid line, ${\sim }4\times 10^5$; blue solid line, ${\sim }5\times 10^5$; and brown solid line, ${\sim }6.7\times 10^5$. (a) Effect of Reynolds number for different roughness. (b) Effect of roughness for different Reynolds number. Note that successive sequences of curves have been offset in pressure coefficient by $-0.1$.

Figure 7(b) gives the variation of $\sigma _{C_P}$ with roughness for various Reynolds numbers. For a given Reynolds number, $\sigma _{C_P}$ increases over the circumference of the cylinder with an increase in roughness. In addition, the peak in $\sigma _{C_P}$ increases and moves upstream as roughness is increased for a fixed Reynolds number. This change is similar to that seen when Reynolds number is increased for a fixed roughness.

3.4. Power spectra of lift and Strouhal number of vortex shedding

Figure 8(a) gives the power spectral density (PSD) of fluctuations in the lift coefficient at a Reynolds number of $6.7\times 10^5$ for different roughnesses. A similar distribution with a significant peak is seen in the majority of the tests (all at postcritical Reynolds numbers) indicating the presence of strong periodic vortex shedding. Since the lift force is induced by the alternating vortex shedding, the second half of the lift cycle must mirror the first half, which means only odd harmonics can contribute to a periodic signal. This can be seen in the presence of the third harmonic throughout the postcritical regime.

Figure 8.

(a) Frequency spectra of the lift coefficient for different roughnesses at Reynolds number of $6.7\times 10^5$: red, $k_s/D=3\times 10^{-3}$; green, $k_s/D=1.9\times 10^{-3}$; blue, $k_s/D=1.4\times 10^{-3}$; brown, $k_s/D=1.1\times 10^{-3}$. (b) Coefficient of pressure vs time on $k_s/D=1.4\times 10^{-3}$ at Reynolds number of $1.64\times 10^5$. (c) Spectra of $C_L$ for different time intervals. (d) Time history of $C_L$ and $C_D$ of that test.

Achenbach & Heinecke (Reference Achenbach and Heinecke1981) found that energy of lift fluctuations is distributed in a narrow band of frequencies for rough cylinders through the critical regime, while on the other hand Szechenyi (Reference Szechenyi1975) and Batham (Reference Batham1973) found a broadband spectra without an obvious dominant frequency near the critical Reynolds number. A clear shedding frequency was found in the lift spectra for all tests except for $k_s/D=1.4\times 10^{-3}$ and $k_s/D=1.1\times 10^{-3}$ at Reynolds numbers near $Re\sim 2\times 10^5$. As an example, gives time histories of the coefficients of pressure, lift and drag (plotted against a non-dimensional convective time scale, $tU_{\infty }/D$, also referred to as $t^*$ henceforth) observed for $k_s/D=1.4\times 10^{-3}$ at a Reynolds number of $1.64\times 10^5$ are given in figures 8(b), 8(c) and 8(d), respectively.

For $0< t^*\leq 1200$, a stable LSB exists on both sides of the cylinder, which can be inferred from the lower mean $C_D$ and mean $C_L$ of ${\sim }0$. The presence of the LSB delays separation, increases the base pressure and, hence, decreases $C_D$. For $t^*>1200$, the LSB near ($\theta \sim (300^{\circ }$–$250^{\circ })$) becomes unstable and intermittent leading to increased $C_D$ and a non-zero mean $C_L$. The onset of instability is found to occur over the entire span but since the LSB becomes intermittent, the separation line in the spanwise direction at a given instant of time is expected to be jagged and, hence, vortex shedding is incoherent (Bearman Reference Bearman1984). This is also seen in the frequency spectra of the sectional lift coefficient from two different periods, $0< t^*\leq 1200$ and $2500< t^*\leq 3700$. A dominant frequency is present in the spectrum when the LSB is stable on both sides of the cylinder, while the spectrum resulting from an asymmetric intermittent LSB is broad range. The spectrum for the entire duration of the test ($t^*=7500,t=120\ {\rm s}$) is broadband in nature and, hence, these Reynolds numbers were excluded from figure 10 despite there being strong periodicity over a short period. In addition, the Strouhal number pertaining to the wake flow when there is a dominant frequency or a narrow band in the energy spectrum while in the ‘two-bubble’ state is higher than the Strouhal numbers in both subcritical and postcritical regimes and is ${\sim }0.32$. Bearman (Reference Bearman1969) also found a higher frequency in the ‘two-bubble’ state.

This intermittent LSB is absent for the two rougher cylinders ($k_s/D=1.9\times 10^{-3}$ and $k_s/D=3\times 10^{-3}$) in the current tests. Thus, the prevalence of an intermittent LSB reduces as the roughness is increased, i.e. the supercritical regime becomes smaller as the roughness is increased. In other words, surface roughness is found to promote coherent shedding in the Reynolds number space (in agreement with Achenbach & Heinecke Reference Achenbach and Heinecke1981).

The Strouhal number of the vortex shedding initially increases and then decreases with the Reynolds number, similar to the changes in wake angle and base pressure. This variation of Strouhal number with Reynolds number for different roughnesses is given in figure 10(a). For a given roughness, the Strouhal number decreases with an increasing Reynolds number in the postcritical flow, indicating that the wake width increases (Roshko Reference Roshko1961). This increase is a consequence of the upstream movement of the separation angle and results in reduced base pressure and, thus, increased drag. An increase in roughness at a given postcritical Reynolds number also increases wake width and, hence, decreases the Strouhal number. Current data also confirm the prediction of Achenbach & Heinecke (Reference Achenbach and Heinecke1981) that the postcritical Strouhal numbers for rough cylinders are smaller than those for smooth cylinders. In line with the asymptotic behaviour of separation angle, base pressure and coefficient of drag, the Strouhal number eventually approaches asymptotic values at large Reynolds numbers (${\sim }0.2$ for the roughest surface tested and ${\sim }0.21$ for the smoothest).

Two proposed universal Strouhal numbers: the Roshko number, $St_R$, (Roshko Reference Roshko1954, Reference Roshko1961) and the Bearman number, $St_B$, (Bearman Reference Bearman1967) were computed for the current tests and the results are presented in figure 9. While the Roshko number uses wake width and velocity near the separation point, the Bearman number makes use of lateral vortex separation and velocity near the separation point as the characteristic length and velocity scales, respectively. The Roshko number (Roshko Reference Roshko1954) is calculated as

(3.1)\begin{equation} St_R =\frac{f h_{s}}{U_s}, \end{equation}

where $f$ is the frequency of shedding, $U_s$ is the velocity at the edge of the boundary layer near the separation, and $h_{s}$ is the lateral (cross-stream) spacing between the shear layers when they become parallel. Here $U_s$ can be estimated through Bernoulli's equation as

(3.2)\begin{equation} U_s=U_{\infty}(1-C_{P_b})^{0.5}. \end{equation}

From simple momentum considerations:

(3.3)\begin{equation} - C_{P_b} h_{s}= {C_D D}. \end{equation}

On the other hand, the Bearman number (Bearman Reference Bearman1967) is

(3.4)\begin{equation} St_B =\frac{f b}{U_s}, \end{equation}

where $b$ is the lateral spacing between the centres of vortices of the same sign. Here $f$ is the frequency of shedding, $a$ is the longitudinal spacing between vortex centres, $U_{Vb}$ is the velocity of vortex centres relative to the body (stationary cylinder in this investigation) and $U_{Vf}$ is the velocity of vortex centres relative to the freestream ($U_{\infty }=U_{Vf}+U_{Vb}$). From (3.4),

(3.5)\begin{equation} \left.\begin{gathered} St_B= \frac{f b a}{a U_{\infty}(1-C_{P_b})^{0.5}},\\ f a = U_{Vb},\\ St_B = \frac{b}{a}\frac{U_{Vb}}{U_{\infty}}\frac{1}{(1-C_{P_b})^{0.5}}. \end{gathered}\right\} \end{equation}

Figure 9.

The length and velocity scales used in the calculation of universal Strouhal numbers, $St_R$ and $St_B$; red dashed line, mean shear layers.

Figure 10.

(a) Strouhal number and (b) the Roshko number (top), $St_R$, and the Bearman number (bottom), $St_B$, for different roughnesses. Confidence intervals were calculated as described in § 2.2. Plots: ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red), $k_s/D=3\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacktriangle }\ {\cdot }\ {\cdot }$ (green), $k_s/D=1.9\times 10^{-3}$; ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ (blue), $k_s/D=1.4\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown), $k_s/D=1.1\times 10^{-3}$.

Kronauer's stability criterion states that the vortex street aligns itself such that the vortex-street drag coefficient, $C_{D_S}$, is minimum with respect to the aspect ratio, $b/a$. This criterion can be simplified to

(3.6)\begin{equation} \frac{b}{a}\frac{U_{Vb}}{U_{\infty}} = F \left( C_D\, St\right). \end{equation}

where $F$ is a function resulting from the stability criterion. Further information on the evaluation of the Bearman number is given in Appendix A.2.

Thus, the Roshko and the Bearman numbers for a given Reynolds number can be estimated using the coefficient of drag, $C_D$, the Strouhal number of shedding, $St$, and the base pressure coefficient, $C_{P_b}$. In these calculations of $St_R$ and $St_B$, measured values (and not blockage-corrected ones) of $C_D$, $St$ and $C_{P_b}$ are used, since the influence of blockage and blockage corrections on the vortex street is uncertain (Bearman Reference Bearman1967). The variation of $St_R$ and $St_B$ with Reynolds number for various roughnesses is given in figure 10(b).

Over the range of Reynolds numbers and roughnesses tested, $St_B$ has less scatter than $St_R$. The values of $St_R$ and $St_B$ were found to be ${\sim }0.14$ and ${\sim }0.17$ in excellent agreement with those found by Adachi (Reference Adachi1997) at similar Reynolds numbers on rough cylinders. The scatter in both $St_R$ and $St_B$ increases in the critical regime owing to uncertainties of measurements. Moreover, a slight downward trend in $St_R$ is found with increasing Reynolds number suggesting that perhaps $St_R$ is not truly universal. On the other hand, the variation in the postcritical regime is still small over the Reynolds number range considered but there is a noticeable spread with roughness. It is of note that the tests in the supercritical regime where periodic shedding is sporadic are omitted in these calculations.

3.5. Spanwise correlation of the lift

The one-sided, axial correlation length of lift $\varLambda$ is determined following the procedure outlined in § 2.1 of Norberg (Reference Norberg2003) and the results are given in figure 11. A sample calculation for the correlation length is given in Appendix A. Owing to the sparse spanwise distribution of pressure measurements, there is some scatter in the calculated axial correlation length. Despite the scatter, it is clear that $\varLambda$ does not vary significantly with roughness or Reynolds number in the postcritical regime. Broadly, $\varLambda$ takes the value of ${\sim }3D$ in the subcritical regime and drops to ${\sim }1.5D$ in the critical regime indicating a drop in coherence due to the intermittent separation. In the postcritical regime, $\varLambda$ is ${\sim }4D$ for all the roughnesses tested. These results are in excellent agreement with Buresti (Reference Buresti1981) where correlation lengths were found using hot-wire measurements. This agreement is surprising given the difference in aspect ratios between the two set-ups and the method of measurement. As mentioned previously, correlation lengths of ${\sim }3.2D$ and ${\sim }3.9D$ were found at particular postcritical $Re$ by Batham (Reference Batham1973) ($AR = 6.6$), Ribeiro (Reference Ribeiro1991) ($AR = 6$), respectively, and the current results are in good agreement with them. However, Eaddy (Reference Eaddy2019) reported correlation lengths of ${\sim }2.5\unicode{x2013} 3.4D$ for an aspect ratio of 9 and $6D$ for an aspect ratio of 5.7. The turbulence intensity of the free stream in Eaddy (Reference Eaddy2019) was $4.4\,\%$, and this could be the cause of the slightly lower correlation lengths for the larger aspect ratio set-up. It is interesting that an $AR$ of 5.7 in Eaddy (Reference Eaddy2019), which is similar to that in Ribeiro (Reference Ribeiro1991) and Batham (Reference Batham1973), resulted in a much higher correlation length. An increased blockage and vibration in their low aspect ratio set-up could also contribute to this discrepancy. The difference in fluctuating lift coefficient between the two set-ups supports this hypothesis.

Figure 11.

Axial correlation length of lift for different roughness and Reynolds numbers. Confidence intervals were calculated as described in § 2.2. Plots: $\star$ (red), $k_s/D=3\times 10^{-3}$; $\blacktriangle$ (green), $k_s/D=1.9\times 10^{-3}$; $\bullet$ (blue), $k_s/D=1.4\times 10^{-3}$; $\blacklozenge$ (brown), $k_s/D=1.1\times 10^{-3}$.

A correlation length of ${\sim }4D$ thus appears to be the best estimate for postcritical flows over rough cylinders. This length is significantly larger than the $\varLambda \sim 1.5D$ for smooth cylinders at similar Reynolds numbers (Batham Reference Batham1973; King Reference King1977; Blackburn & Melbourne Reference Blackburn and Melbourne1996), indicating that the roughness increases spanwise uniformity of the flow in the Reynolds number range of $Re=3\times 10^5$ to $6.5\times 10^5$. Schewe (Reference Schewe1983) showed that the transition to the postcritical regime for smooth cylinders begins at $Re=2.5\times 10^6$. Hence, it is likely that the smooth cylinder results of correlation lengths at $3\times 10^5\leq Re \leq 6.5\times 10^5$ were obtained in flow regimes that contain LSBs, thus explaining the lower correlation lengths. While the difference in axial correlation length of lift between smooth and rough cylinders at the same Reynolds number is significant, all roughnesses tested showed similar correlation lengths implying that the magnitude of the roughness has little effect on the extent of spanwise correlation in the range of Reynolds numbers tested.

3.6. On behaviour of the flow beyond $Re\sim O(10^6)$

The largest Reynolds number tested in the current work is $6.7\times 10^5$ and all of the variables measured, i.e. $C_D$, $\sigma _{C_L}$, $C_{P_b}$, $C_{P_m}$, $\theta _w$, $St$ and $\varLambda$, appear to have reached or are close to their asymptotic values with respect to increasing Reynolds number. This observation is in agreement with those of Güven et al. (Reference Güven, Farell and Patel1980), Buresti (Reference Buresti1981) and Nakamura & Tomonari (Reference Nakamura and Tomonari1982) up to the largest $Re$ tested in those works. Shih et al. (Reference Shih, Wang, Coles and Roshko1993) and Adachi (Reference Adachi1997) investigated rough cylinders at Reynolds numbers up to $O(10^7)$ and observed no evidence of the drag curve turning over as the Reynolds number was increased further towards the upper limit of those experiments.

On the other hand, the uncorrected drag coefficient, $C_D$ in Achenbach (Reference Achenbach1971) for $k_s/D=9\times 10^{-3}$ decreased from ${\sim }1.3$ at $Re\sim 3\times 10^6$ to ${\sim }1.2$ at $Re\sim 3\times 10^7$. The magnitude of decrease in $C_D$ was smaller in the blockage corrected drag coefficients, ${\sim }1.04$ at $Re\sim 3\times 10^6$ to ${\sim }1$ at $Re\sim 3\times 10^7$. In addition, van Hinsberg (Reference van Hinsberg2015) found that for larger Reynolds numbers, $C_D$, $\sigma _{C_L}$, $St$ and to a minor extent $C_{P_b}$ and $C_{P_m}$ reached a peak before decreasing slightly beyond $Re\sim 10^6$. However, these trends were found to occur only with the data obtained from the flow generated through the larger total pressures (i.e. higher Mach numbers).

For a fixed diameter, larger Reynolds numbers result in larger Mach numbers, thus increasing the effect of compressibility of the working fluid. Jones et al. (Reference Jones, Cincotta and Walker1969) investigated Reynolds numbers from $0.4\times 10^6$ to $14\times 10^6$ on smooth cylinders at Mach numbers ranging from 0.1 to 0.6. $C_D$ vs $Re$ for Mach numbers above $M>0.2$ showed the drag reaching a peak prior to remaining almost constant or decreasing slightly. Moreover, this behaviour was exacerbated on increasing Mach number. Thus, further investigations as $Re\rightarrow O(10^7)$ over a range of Mach numbers are recommended to understand the influence of compressibility on different flow variables.

3.7. The roughness Reynolds number and curve collapse

In postcritical flows, the influence of an increase in roughness is similar to that of an increase in Reynolds number, i.e. the minimum pressure, $C_{P_m}$, increases while base pressure, $C_{P_b}$, and wake angle, $\theta _w$, decrease. From figure 6, it is also clear that $C_{P_b}$ and $\theta _w$ approach asymptotic values with increasing roughness similar to the variation with increasing Reynolds number. The peak in the fluctuating pressure distribution moves upstream and $\sigma _{C_P}$ in the downstream region of the cylinder increases with increasing roughness, and these changes too are qualitatively similar to those that occur with increasing Reynolds number. On the other hand, axial correlation length is ${\sim }4D$ in the postcritical regime for all roughnesses tested and, hence, the magnitude of spanwise correlation of forces is the same for all roughnesses tested in postcritical flow.

The variation in all the above-mentioned properties is similar whether it is a result of a change in Reynolds number or a change in roughness. This, combined with the difficulty of achieving postcritical Reynolds numbers while maintaining acceptable blockage and aspect ratio in most wind tunnels provides the support for the use of roughness to simulate the effect of postcritical flow proposed by Szechenyi (Reference Szechenyi1975).

Figure 12 gives the variation of bulk properties, mean drag and fluctuating lift as functions of Roughness Reynolds number, $Re_{k_s}={(\rho U_{\infty } k_s)}/{\mu }=Re(k_s/D)$. In postcritical flows and for a given Roughness Reynolds number, the maximum deviation from the mean $C_D$ among different roughnesses tested is only ${\sim }3\,\%$. While the corresponding difference in the fluctuating coefficient of lift is higher (within $10\,\%$), this is of the order of the experimental error in predictions of $\sigma _{C_L}$ as seen in figure 12(b).

Figure 12.

(a) Mean drag coefficient and ($b$) fluctuating lift coefficient as a function of Roughness Reynolds number: ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red), $k_s/D=3\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacktriangle }\ {\cdot }\ {\cdot }$ (green), $k_s/D=1.9\times 10^{-3}$; ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ (blue), $k_s/D=1.4\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown), $k_s/D=1.1\times 10^{-3}$.

Figure 13 gives the mean and fluctuating pressure distribution from different roughnesses at varying Reynolds numbers but at the same Roughness Reynolds number of 720. It is evident that the differences in mean $C_P$ are only in the acceleration region and $C_P$ nearby and postseparation is similar for all roughnesses. In the fluctuating pressure distribution, the peak of $\sigma _{C_P}$ occurs near the same azimuthal angle. However, quantitative differences in $\sigma _{C_P}$ in the downstream region are larger than those in the mean $C_P$ and these contribute towards the differences in $\sigma _{C_L}$.

Figure 13.

Circumferential distributions of (a) mean pressure and (b) fluctuating pressure coefficients at Roughness Reynolds number of $720$: $\star$ (red), $k_s/D=3\times 10^{-3}$; $\triangle$ (green), $k_s/D=1.9\times 10^{-3}$; $\bigcirc$ (blue), $k_s/D=1.4\times 10^{-3}$; $\lozenge$ (brown), $k_s/D=1.1\times 10^{-3}$.

Mean base pressure, $C_{P_b}$, wake angle, $\theta _w$, the total contribution of base $C_P$ to the drag coefficient, $C_{D_{base}}$, and the contribution of upstream $C_P$ to the drag coefficient, $C_{D_{rest}}$, Strouhal number, $St$, and the axial correlation length, $\varLambda$, are plotted against Roughness Reynolds number in figure 14. The wake angle, which, as described previously is representative of the separation angle in the postcritical regime, is fairly constant at a given Roughness Reynolds number irrespective of the roughness used to achieve it. As can be seen in figure 6(f), $C_{P_b}$ is a strong function of $\theta _w$. Consequently, the base pressure and the contribution of the pressure distribution in the base region to drag is constant for a given Roughness Reynolds number. The contribution of the upstream region of drag is a function of roughness since flow in the acceleration region and $C_{P_m}$ is a function of roughness even at large Reynolds numbers. However, this contribution is minor when compared with the contribution of base pressure, leading to only a minor deviation in the total drag coefficient.

Figure 14.

Variation of (a) wake angle, (b) base pressure coefficient, (c) base pressure contribution to drag, (d) upstream pressure contribution to drag, (e) Strouhal number and (f) axial correlation length of lift with roughness Reynolds number: ${\cdot }\ {\cdot }\ {\star }\ {\cdot }\ {\cdot }$ (red), $k_s/D=3\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacktriangle }\ {\cdot }\ {\cdot }$ (green), $k_s/D=1.9\times 10^{-3}$; ${\cdot }\ {\cdot }\ $$\bullet$$\ {\cdot }\ {\cdot }$ (blue), $k_s/D=1.4\times 10^{-3}$; ${\cdot }\ {\cdot }\ {\blacklozenge }\ {\cdot }\ {\cdot }$ (brown), $k_s/D=1.1\times 10^{-3}$.

Since the separation angle, drag coefficient and base pressure collapse with Roughness Reynolds number, it follows that wake parameters also collapse with roughness Reynolds number thereby leading to a collapse of the Strouhal number. Strouhal number found from spectral peaks of the lift fluctuations is plotted against roughness Reynolds number in figure 14(e).

To summarise, the mean drag coefficient and the Strouhal number collapse well when plotted against roughness Reynolds number, since wake ($\sim$ separation) angle and consequently, base pressure and wake width collapse with roughness Reynolds number. On the other hand, the minimum pressure and the fluctuating lift coefficient are more sensitive to local flow perturbations and, hence, different roughness levels and Reynolds numbers lead to differences in $\sigma _{C_L}$.

However, the asymptotic values of the base pressure, and the separation angle in postcritical flows for smooth cylinders (from Güven et al. Reference Güven, Farell and Patel1980) are different from those of rough cylinders in the current tests. A collapse of the drag coefficient with roughness Reynolds number that includes data from smooth cylinders is hence expected to have a larger deviation than found by Güven et al. (Reference Güven, Farell and Patel1980). Moreover, axial correlation lengths for smooth cylinders in postcritical flows are unknown and the similarity among spanwise flow over smooth and rough cylinders in postcritical flows is still uncertain.

Thus, the use of roughness Reynolds number is recommended in instances for which postcritical flow of a slightly rough cylinder is simulated using a rougher cylinder at a lower Reynolds number. Since the deviation in the collapse of $C_D$ through roughness Reynolds number is only from the minimum pressure region, this collapse would work well if the roughnesses tested have similar characteristics and cause similar deceleration in the flow. This explains the collapse of $C_D$ observed in Szechenyi (Reference Szechenyi1975) (since all the roughnesses were generated from glass beads) and the current work, and the deviations observed when different roughnesses were taken into account in Güven et al. (Reference Güven, Farell and Patel1980). The comparisons in Güven et al. (Reference Güven, Farell and Patel1980) were also from flow set-ups of different geometrical properties and investigations that attempt the curve collapse while incorporating different kinds of roughness elements in the same set-up are required to further identify the limitations to the curve collapse using roughness Reynolds number.

Szechenyi (Reference Szechenyi1975) proposed three thresholds in the roughness simulation i.e. $Re_{\delta }\sim 200$ as the lower limit for the return of coherent vortex shedding, $Re_{\delta }\sim 1000$ as the lower limit after which the coefficients of drag, lift and the Strouhal number remain fairly constant, and a relative roughness ratio of $\delta /D=2.2\times 10^{-3}$ (where $\delta$ is the diameter of the glass beads used to generate roughness) as the upper limit after which the coherence in vortex shedding breaks down. For the roughnesses tested in the current study, the lower limit of $Re_{k_s}$ at which the coherent shedding reestablishes intermittently is ${\sim }300$ while the steady nature (i.e. less uncertainty in the estimates) of the fluctuating lift coefficient, Strouhal number and the axial correlation length of lift are established at ${\sim }500$. As mentioned previously, increase in roughness in the current experiments stabilises vortex shedding rather than disrupting it and coherent vortex shedding is seen at all Reynolds numbers for relative roughness, $k_s/D = 3.1\times 10^{-3}$. Moreover, Buresti (Reference Buresti1981) found coherent shedding with relative roughness as high as $k/D=12\times 10^{-3}$. This discrepancy among the observations is probably due to the use of glass beads in Szechenyi (Reference Szechenyi1975) to generate roughness while sandpaper was used in Buresti (Reference Buresti1981) and the current experiments.

3.8. Intermediate wake measurements

Mean and fluctuating velocity profiles and the PSD of velocity at 3 diameters downstream of the 40 grit cylinder are given in figure 15. These are measured using a single-axis hot-film anemometer with its axis parallel to the axis of the cylinder and, hence, the hot wire is sensitive to the total in-plane velocity. This total in-plane velocity is denoted by $V$ while $y$ is the cross-stream distance from the centre of the cylinder.

Figure 15.

Mean, fluctuating in-plane velocity distribution and spectra of fluctuations at point of maximum $\sigma _V$ in the wake of the cylinder of roughness, $k_s/D=3\times 10^{-3}$: black, $Re\sim 1.9\times 10^5$; red, $Re\sim 3.8\times 10^5$.

Figure 16.

Mean, fluctuating in-plane velocity distribution and spectra of fluctuations at point of maximum $\sigma _V$ in the wake at, $Re\sim 3.8\times 10^5$: black, $k_s/D=3\times 10^{-3}$; red, $k_s/D=1.1\times 10^{-3}$.

For a fixed roughness, the mean velocity in the wake decreases with an increase in Reynolds number and this increase in the velocity deficit leads to higher drag. Fluctuations in the velocity increase with increasing Reynolds number, albeit at a lower rate than the mean velocity. Power spectra of the velocity fluctuations (at the point at which fluctuating velocity is maximum) show that energy content over the entire frequency range is higher for the larger Reynolds number tested. Similar to the observation from $C_L$ spectra, Strouhal number of the dominant frequency decreases slightly as the Reynolds number increases in the postcritical regime.

Velocity profiles and spectra downstream of two different roughnesses but at the same Reynolds number are given in figure 16. The mean velocity deficit is similar for the two roughnesses while the wake width is slightly smaller for the lower roughness. Consistent with the fluctuating lift coefficient, $\sigma _{C_L}$, and the fluctuating coefficient of pressure, $\sigma _{C_P}$, the fluctuating velocity shows a clear increase with increasing roughness, indicating an increase in the turbulent kinetic energy. While the energy density over the broad frequency range is similar for both roughnesses, the dominant shedding frequency has more energy for the larger roughness, possibly because this roughness is well into the postcritical regime. This shows that at a given Reynolds number, energy fluctuations are larger for the larger roughness and that the increased energy is concentrated predominantly at the shedding frequency.

Wake profiles for the cylinders with relative roughness $k_s/D=1.9\times 10^{-3}$ and $k_s/D=1.1\times 10^{-3}$ through the near and intermediate wake are given in Appendix A.

3.9. Wake frequencies

Figure 17 shows the PSD of velocity fluctuations at different downstream locations in the wake for two roughnesses, $k_s/D=1.9\times 10^{-3}$ and $k_s/D=1.1\times 10^{-3}$, at $Re_{k_s}\sim 550$. At each of these locations, a spectrum is obtained from the time history of in-plane velocity at a point where $\sigma _{V}/V_{ref}$ is maximum in the cross-stream profile. The energy in fluctuations before separation is lower than that postseparation over the entire frequency range. Spectra in the shear layer (at $0.25D$, $0.5D$ and $1D$) have the highest energy among the measurement range and, moreover, a plateau in the PSD is found at higher frequencies of $fD/U_{\infty }\sim 1\unicode{x2013} 3$. These frequencies also had a higher spatial amplification factor, $\alpha$, Khor, Sheridan & Hourigan (Reference Khor, Sheridan and Hourigan2011) confirming that these are the frequencies at which shear-layer instabilities grow fastest. Furthermore, as one moves downstream, the frequency in the shear layers reduces slightly indicating an increase in shear-layer thickness. A similar plateau is found at postcritical Reynolds numbers for smooth cylinders in Lehmkuhl et al. (Reference Lehmkuhl, Rodríguez, Borrell, Chiva and Oliva2014) and was considered a signature of Kelvin–Helmholtz frequencies, $f_{KH}$, in the shear layer. While shear-layer frequencies in the smooth cylinder follow the power law suggested by Prasad & Williamson (Reference Prasad and Williamson1997) ($\,f_{KH}/f_{V} \propto Re^{0.67}$), $f_{KH}$ in the current results is an order of magnitude lower for the same Reynolds number. For instance, at a Reynolds number of $3.8\times 10^5$, the power law for smooth cylinders predicts $f_{KH} D/U_{\infty }\sim 30$ while the current results show the broadband (non-dimensional) frequency between 1 and 3.

Figure 17.

Frequency spectra of velocity fluctuations in the wake: (a) $k_s/D=1.9\times 10^{-3}$ at $Re=2.9\times 10^5$ and $Re_{k_s}=\sim 550$ and (b) $k_s/D=1.1\times 10^{-3}$ at $Re=4.7\times 10^5$ and $Re_{k_s}=\sim 510$. Spectra obtained at the location of the cross-stream maximum velocity fluctuation at distance downstream from the centre of the cylinder: black, $0D$; green, $0.25D$; blue, $0.5D$; red, $1D$; brown, $6D$.

To further investigate this deviation, the momentum thickness of the shear layer, $\varTheta$ was computed according to the procedure outlined in Khor et al. (Reference Khor, Sheridan and Hourigan2011) and the results are tabulated in table 3. Since the hot-film anemometer measures the total in-plane velocity, current values of momentum thickness are expected to be only approximate. The key takeaway however, is that the momentum thickness of the shear layers for rough cylinders is an order of magnitude higher than that of the predicted smooth-cylinder momentum thickness, $\sim$0.003 at $0.5D$ according to the correlation given in Khor et al. (Reference Khor, Sheridan and Hourigan2011) at the same Reynolds number. Since the boundary-layer thickness is larger on rough surfaces than on smooth surfaces for a given postcritical Reynolds number, separated shear layers are also expected to be thicker.

Table 3.

Momentum thickness ($\varTheta /D$) of the shear layer at different streamwise locations.

The empirical power-law correlations of $f_{KH}$ and $\varTheta /D$ vs $Re$ for smooth cylinder flows do not contain data from the postcritical regime where shear layers are expected to be turbulent and, hence, thicker than laminar shear layers. Moreover, as the Reynolds number increases, the energy content of the turbulent shear layer is expected to be distributed over a wider range of frequencies thereby making it difficult to discern an exact value for $f_{KH}$. However, current predictions of momentum thickness agree remarkably well with those of shear-layer frequencies when the inverse proportionality between the frequency and shear-layer thickness is taken into account, i.e. while the frequency peak of shear layers is an order of magnitude smaller than that obtained from the smooth cylinder correlations, the momentum thickness is an order of magnitude larger.