Wind Tunnel Study on Spanwise Correlation of Aerodynamic Forces on a 5:1 Rectangular Cylinder

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1 The Eighth Asia-Pacific Conference on Wind Engineering, December 10 1, 2013, Chennai, India Wind Tunnel Study on Spanwise Correlation of Aerodynamic Forces on a 5:1 Rectangular Cylinder Xiaobing Liu 1, Yan Cui 2, Qingkuan Liu 3. 1 Lecturer, Shijiazhuang Tiedao University, Shijiazhuang, Hebei, China, x_b_liu@126.com 2 Post graduate student, Shijiazhuang Tiedao University, Shijiazhuang, Hebei, China, @qq.com 3 Professor, Shijiazhuang Tiedao University, Shijiazhuang, Hebei, China, lqk@stdu.edu.cn ABSTRACT Spanwise correlation of aerodynamic forces on a 5:1 rectangular cylinder were investigated through wind tunnel test in smooth flow at wind attacking angle of. The test results show that decay of spanwise correlation coefficient is slower for lift than for drag. Spanwise correlation coefficient of tap pressure on upper side of cylinder decay in a various degree. When Δ/D (Δ is space along coming wind, D is height of rectangular cylinder) around 0. or 3.75, the decay is slow. When Δ/D is around 2 or.95, the decay is rapid. Keywords: Spanwise correlation, Aerodynamic forces, Rectangular cylinder, Wind tunnel test Introduction It is known that when the vortex-shedding frequency is close to the natural frequency of the body, it can cause vortex- induced resonance. Although vortex-induced vibration (VIV) is a kind of limited amplitude vibration and does not directly cause the collapse of a bridge, it can result in large displacements and discomfort to the drivers. In addition, VIVs commonly occur at low wind speeds, so the occurrence probability of VIV is high, resulting in long-term fatigue damage. At present, most of theoretical model study on VIV assumes that flow around bridge deck is two dimensional, the spanwise correlation of aerodynamic forces on bridge deck is ignored. This may be one reason why VIV amplitude gotten from wind tunnel does not agree well with VIV amplitude gotten from theoretical calculation. As a typical bluff body, the flow characteristics of rectangular cylinder has been investigated by many researchers[1-5]. Among these research, more attention was paid to flow bulk parameters (e.g. aerodynamic force coefficients per unit length or Strouhal number) or sectional distribution of pressure statistics (e.g. mean value and standard deviation). Less attention was paid to spanwise correlation of aerodynamic forces on rectangular cylinder. In present paper, wind tunnel test was performed to study spanwise correlation of aerodynamic forces on a stationary 5:1 rectangular cylinder. This work has made first step for study spanwise correlation of aerodynamic forces on rectangular cylinder in voetex-induced vibration. Wind Tunnel Test Wind tunnel test was conducted in high-speed test section of STU-1 boundary layer wind tunnel. The section is 5 meters long, 2.2meters wide and 2 meters high. The test model which is made of organic glass is 2 meters long with a cross section of 0.3m 0.06m(B D). The model was instrumented with 80 pressure taps arranged in eight arrays of 60 (23 on each side face and 7 on the windward and leeward faces) as shown in Fig. 2 and Fig. 3. The arrays Proc. of the 8th Asia-Pacific Conference on Wind Engineering Nagesh R. Iyer, Prem Krishna, S. Selvi Rajan and P. Harikrishna (eds) Copyright c 2013 APCWE-VIII. All rights reserved. Published by Research Publishing, Singapore. ISBN: doi: /

2 are located at following distance from central section: array#1: -80 cm; array#2: -0 cm; array#3: -20 cm; array#: -5 cm; array#5: centralsection; array#6: +10cm, array#7: +30cm; array#8: +80cm. This allows evaluating the spanwise correlation of aerodynamic pressure for different spanwise space. The test model is stationary. The wind speed is 10m/s. The coming flow is uniform flow and turbulence intensity is about 0.5%. The wind attacking angle is from to 1, changing step is 1. Fig.1 Photo of test model Fig.2 Pressure tap location in plan view Fig.3 Pressure tap location in cross section Aerodynamic Coefficient and Strouhal Number Mean and standard-deviation values of pressure coefficient in the middle span section for upper and lower side of model at wind attacking angle are shown in Figure and Figure 5. It can be seen that the mean and standard-deviation values of pressure coefficient for upper side agree well with those for lower side. In Table 1, Reynolds number, drag coefficient 212

3 and Strouhal number gotten from present paper are compared with those gotten from other paper. It can be seen that test results in present paper are in good agreement with those in other paper. This shows that the test data in present paper is correct. upper side lower side upper side lower side , mean u s D, r ms s /D s/d Fig. Mean value of pressure coefficient in the middle span section for upper and lower side of modelat wind attacking angle Fig.5 Standard-deviation value of pressure coefficient in the middle span section for upper and lower side of model at wind attacking angle Table 1 Comparision of test results in present paper and in other paper Reynolds number Drag coefficient Strouhal number present test Schewe test Figure 6 shows aerodynamic coefficients of cylinder at different wind attacking angle. It can be seen that the drag coefficient is increasing with increase of wind attacking angle. The lift coefficient gets to maximum value 0.57 at wind attacking angle. Figure 6 shows Strouhal number of cylinder at different wind attacking angle. It can be found that when wind attacking angle is between and, the Strouhal number is around When wind attacking angle is between and 1, the Strouhal number becomes small with increase of wind attacking angle aerodynami c coef f i ci ent Cd Cl Cm St wi nd at t acki ng angl e( ) wi nd at t acki ng angl e( ) Fig.6 Aerodynamic coefficients at different wind attacking angle Fig.7 Strouhal number at different wind attacking angle 213

4 Pressure Coefficient Figure 8 shows pressure coefficients of cylinder surface at different wind attacking angle. From Figure 8(a), it can be found that for windward side of cylinder, the pressure coefficient of lower half part becomes big with increase of wind attacking angle, while the pressure coefficient of upper half part becomes small with increase of wind attacking angle. From Figure 8(b), it can be found that pressure coefficient of leeward side of cylinder becomes small with increase of wind attacking angle. It can be found from Figure 8(c) that with increase of wind attacking angle, the maximum pressure coefficient of upper side of cylinder becomes small. It can be seen from Figure 8(d) that with increase of wind attacking angle, the maximum pressure coefficient of lower side of cylinder changes little, while the position corresponding to the maximum pressure coefficient changes significantly h/b h/b (a) windward side (b) leeward side s/b (c) upper side s/b (d) lower side Fig.8 Pressure coefficients of cylinder surface at different wind attacking angle 21

5 Spanwise Correlation of Aerodynamic Forces The Spanwise correlation coefficient of aerodynamic forces at wind attacking angle are shown in Figure 9, where δ represents spanwise space. It can be found that spanwise correlation coefficients of drag, lift and torque become small with increase of spanwise space. For the same spanwise space, spanwise correlation coefficient of drag is smallest and spanwise correlation coefficient of lift is biggest. In other words, the decay of spanwise correlation coefficient is slower for lift than for drag correl at i on coef f i ci ent dr ag lift torque /D Fig.9 Spanwise correlation coefficient of aerodynamic forces at wind attacking angle /D /D Fig.10 Spanwise correlation coefficient of tap pressure for upper side of the model at wind attacking angle 215

6 correl at i on coef f i ci ent /D Fig.11 Spanwise correlation coefficient of tap pressure for different Δ/D and same spanwise space δ/d=18.33 Figure 10 shows spanwise correlation coefficient of tap pressure for upper side of the model at wind attacking angle. Figure 11 shows spanwise correlation coefficient of tap pressure for different upper side location(different Δ/D) and same spanwise space δ/d= In these two figures, δ represents spanwise space and Δ represents space along coming wind. It can be found from these two figures that spanwise correlation coefficient of tap pressure become small with increase of spanwise space, however, for different Δ/D, the spanwise correlation coefficient of tap pressure differs from each other even for the same spanwise space δ/d. In other words, spanwise correlation coefficient of tap pressure decay in a various degree. When Δ/D is around 0. or 3.75, the decay is slow. When Δ/D is around 2 or.95, the decay is rapid. Conclusions Spanwise correlation of aerodynamic forces on a 5:1 rectangular cylinder were investigated through wind tunnel test in smooth flow at wind attacking angle of. The test results show that decay of spanwise correlation coefficient is slower for lift than for drag. Spanwise correlation coefficient of tap pressure on upper side of cylinder decay in a various degree. When Δ/D (Δ is space along coming wind, D is height of rectangular cylinder) around 0. or 3.75, the decay is slow. When Δ/D is around 2 or.95, the decay is rapid. References A.J. Bronkhorst. Unsteady pressure measurements on a 5:1 rectangular cylinder[c]. // Proceedings of the 13th International Conference on Wind Engineering. Amsterdam, Holland, 2011, Gianni Bartoli. Wind tunnel study on the aerodynamics of a 5:1 rectangular cylinder in smooth flow[c]. //Proceedings of the 13th International Conference on Wind Engineering. Amsterdam, Holland, 2011, Ricciardelli. Sectional aerodynamic forces and their longitudinal correlation on a vibrating 5:1 rectangular cylinder[c]. //Proceedings of the 6th International Colloquium on Bluff Bodies, Milano, Italy:

7 Schewe G. Reynolds-Number-Effects in flow around a rectangular cylinder with aspect ratio 1:5[C]. //Proceedings of the 5th European and African Conference on Wind Engineering. Florence, Italy, 2009, Dimet. Effects of the vibration regime on the spanwise correlation of the aerodynamic force on a 5:1 rectangular cylinder [J]. Wind Eng. Ind. Aerodyn. 2010(98):

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