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EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 485 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT Experimental And Numerical Investigation Of The Flow Around The Appendices Of A Whitbread 60 Sailing Yacht P.Planquart, M.Riethmuller (Von Karman Institute for Fluid Dynamics, Belgium) ABSTRACT In this paper, we present results obtained experimentally and numerically during the study of the flow around the appendices of a Whitbread 60 sailing yacht. Experiments are carried out in a wind tunnel on a model of reduced scale (1/15). Force measurements are made using a three component balance. Two different bulbs are tested for different angle of attack. Velocity measurements are made using the P.I.V. technique and a hot wire anemometer. Vortex shedding frequencies are computed from the P.I.V. results and drag values are obtained from the velocity measurements in a plane behind the bulb (wake survey analysis). The experimental results are used to validate the numerical simulations performed using the commercial code FLUENT 5.2. Different turbulence models are compared and a good agreement between the experimental and numerical results was found with the use of the standard k-Îµ turbulence model and wall- functions. INTRODUCTION An experimental and numerical study is actually performed, at the von Karman Institute, on the investigation of the flow around the appendices and the hull of a Withbread 60 (now called VOR 60âin reference to the Volvo Ocean Race). The study combines experiments on a scaled model in a wind tunnel and numerical simulations using the commercial code FLUENT. Wind tunnel experiments have already been used extensively in the past (Tinoco et al 1993, Caponnetto 1993) for the study of IACC appendages and have provided useful information regarding the effect of bulb and winglets on the performance (Claughton et al 1998) of IACC keels. The aim of this research is to validate CFD tools for the design of appendices for a racing sailing yacht. The validation of the numerical simulations is made using the following data: 1. Velocity measurements around the model (mean and instantaneous). 2. Measurement of drag and lift of the appendices using a three-component balance. Two different geometries of bulb have been tested. The first one corresponds to the shape of an existing bulb (Swarbrick 1997) and the second one was designed at the von Karman Institute using simple geometrical shapes. WIND TUNNEL TESTS Description of the facility The experimental investigation is carried out using the scaled model (scale 1/15) represented in figure 1. This model is placed in the wind tunnel L2B of the von Karman Institute (Figure 2). Figure 1âScaled model The section of the wind tunnel is 35*35 cm2 and the maximum velocity that can be reached in the test section is 35 m/s. the authoritative version for attribution. Figure 2âL2 wind tunnel The Reynolds number, when performing wind tunnel tests, is lower than in the real case, but the main

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 486 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT objective of the research is to have a database for validation, and therefore the Reynolds number is not the key parameter. Also, wind tunnel tests allow easy optical access which is an important point when using an advanced optical measurement technique like the Particle Image Velocimetry (P.I.V.). Description of the two geomletries 1. The first bulb, that will be referred as the âexistingâ bulb has been tested in three different configurations represented in the Figure 4. A side view of the âexistingâ bulb is represented in Figure 3. Figure 3âside view of the âexistingâ bulb Figure 4âconfiguration for the âexistingâ bulb 2. The second bulb, designed at the von Karman Institute, consists of a body of revolution created by the combination of an ellipse and a cone. This bulb will be referred as the ânewâ bulb. The comparison between the shape of the âexistingâ bulb and ânewâ bulb is shown in the following figures. Figure 5âcomparison of the two bulbs Figure 6âcomparison of the two bulbs Flow visualization Surface flow patterns observed using oil visualization are footprints of the outer field (Delery 1992). When using the surface oil flow technique, we must first coat the hull and the appendices with a special prepared paint. The air flowing over the surface will carry the oil with it and a streaky deposit of the powder remains to mark the direction of the flow. Using this technique, we are able to analyze the local direction of the flow at the surface and by implication, the general flow structure in the three-dimensional field above it. This information is also used for the validation of skin friction computation. The technique allows determining region of separation and attachment of the flow on an obstacle. This technique has been applied to study the âexistingâ bulb and one result is given in Figure 7 for an angle of attack of 6Â°. Close to the tip of the bulb, painting is accumulating, meaning that the âexistingâ bulb has not an optimal aerodynamic shape. the authoritative version for attribution. Figure 7âOil visualization on the âexistingâ bulb A vortex tube attached at the tip of the bulb has also been observed when the keel is in incidence. This vortex tube has been put in evidence using a small piece of wool that has been translated inside the flow field. By recording the X-Y coordinates of the tube,

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 487 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT we can find the exact position of the vortex tube. Figure 8 shows the rotating wool and we have plot on Figure 9 the position of the vortex tube with respect to the hull, keel and rudder. It is worth mentioning that the vortex tube does not reach the rudder. Figure 9âposition of the vortex tube for an angle of Figure 8âvortex tubeâvisualization. attack of 6Â° P.I.V. measurements The principle of P.I.V. (Lourenzo 1999) is to illuminate particles injected in the flow by a Laser sheet and to observe the scattered light. In order to perform velocity measurements, two Laser pulses, separated by a short and know time interval ât, are emitted to provide two images recorded on the same photographic plate or by a CCD camera providing the image in a numerical form. By measuring the displacement of the particles, the velocity components contained in the plane of the image is deduced in a straightforward manner. P.I.V. is very precious for the study of unsteady phenomena since it allows to freeze the velocity field at a given instant. Mean and instantaneous velocity fields have been recorded in the three planes represented in Figure 10. Figure 10âmeasurement plane for the PIV The measurements have been taken for the three different keel configurations of the âexistingâ bulb. Using the instantaneous data from the Particle Image Velocimetry measurements, we were able to compute the vortex shedding frequencies that characterize the detachment of vortices at the keel. Shedding frequencies for the âexistingâ bulb are given in Table 1. These frequencies should be divided by 45 for the extrapolation to the real case. The frequencies were computed using the distance measured between a negative and a positive peak of vorticity. Knowing the mean velocity, we can compute a first value for the shedding frequency by taking the consecutive distance between two peaks. However, a statistical approach has been used to compute all the possible combination of peaks and different frequencies have been obtained. This approach has been used because two consecutive peaks of vorticity, as shown on the right of Figure 11, might not been the result of two independent vortex shedding. Table 1âfrequencies computed from the PIV results Frequency 1 Frequency 2 Frequency 3 T negative 8070 4040 2630 T positive 9390 4000 2550 Z 7450 3980 2470 Figure 11 shows a typical P.I.V. results measured behind the keel in the plane A represented in Figure 10. On the left side, we see the instantaneous velocity field and on the right side a contour map of vorticity extracted from the instantaneous velocity field using relation (1): the authoritative version for attribution. (1)

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 488 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT Figure 11âInstantaneous velocity field and vorticity Drag and lift measurements Forces on the keel and the bulb (drag and lift) are measured using an in-house three-component balance represented in Figure 12. The keel and the bulb mounted on the balance are represented on Figure 13. Figure 12âSchemativ view of the balance Figure 13âpicture of the experimental set-up (balance+model) Drag curves for the existing bulb as a function of the angle of attack is represented in Figure 14 for the âexistingâ bulb and the new one. For the âexistingâ bulb, the best results are obtained with the configuration T-negative. The worst results are obtained with the configuration T-positive. Comparing the new bulb with the existing one, we observe a decrease in the drag for all angle of attack with the new bulb. Figure 14âDrag value as function of attack Figure 15âLift value as function of angle of attack Lift curves are represented in Figure 15. We observe a rapid increase of the lift for small angles of attack, but starting at 3Â° to 5Â° of angle of attack, depending on the shape of the bulb and the configuration, the lift does not increase anymore due to separation. The flow around the existing keel in configuration T-negative separates for the highest value of angle of attack. The flow around the new bulb starts to separate for 3Â° of angle of attack. These low values of angle of separation can be explained by the high aspect ratio of the keel (Marchaj 1991). Drag has also been computed by measuring the velocity field in two planes located before and behind the keel as the authoritative version for attribution. represented in Figure 16. By computing

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 489 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT the balance of momentum between these two planes, we can deduce the drag using relation (2). The velocity measurements have been performed using a hot wire anemometer mounted on a displacement table. Mean values have been recorded, but also R.M.S. value in order to compute the second term of the right side of equation (2). (2) Figure 16âplane of measurement A typical velocity map (mean value) in the downstream plane for configuration T-negative of the existing bulb is shown Figure 17. This map has been recorded 5 cm behind the tip of the bulb. The free stream velocity is around 34 m/s and the minimum velocity measured behind the bulb is equal to 30 m/s. The R.M.S value of the velocity, in the same plane and for the same configuration, is represented in Figure 18. Figure 18âR.M.S. valueâconfiguration T-negative Figure 17âvelocity magnitudeâconfiguration T- negative The following table shows the value of drag measured by the balance compared with the value computed using the velocity map (wake survey analysis). Table 2âcomparison of drag values for two angle of attack configuration Angle of attack Balance Wake survey analysis DRAG Â° N N T-negative 6 0.54 0.543 T-negative 0 0.436 0.444 T-positive 6 0.636 0.63 T-positive 0 0.466 0.456 Z 6 0.551 0.543 Z 0 0.462 0.438 New bulb 6 0.49 0.506 New bulb 0 0.414 0.398 NUMERICAL SIMULATION Description of the simulations The numerical simulations are performed using the commercial code FLUENTâ¢ 5.2, which solves the Reynolds Averaged Navier-Stokes equations using a finite volume technique. The following turbulence models have been tested in order to determine their influence on the computation of drag and lift: k-Îµ standard model, k-Îµ realizable model and Spalart-Allmaras model. Wall functions are used with the k-Îµ turbulence models. The Spalart-Allmaras turbulence model is a relatively simple one-equation model that solves a modeled transport equation for the kinematic eddy (turbulent) the authoritative version for attribution. viscosity and is well suited for the computational of external flow around aerodynamic shape (Spalart et al, 1994).

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 490 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT The geometry of the âexistingâ bulb has been created using the same CAD file as for the construction of the experimental model in order to avoid geometrical differences. The computational domain is shown in Figure 19. For an angle of attack of 0Â°, a symmetry plane is used to reduce the number of cells. The grid is generated using the commercial grid generator GAMBIT. Figure 20âsurface grid of the keel and the bulb Figure 19âcomputational domain for the numerical simulations A typical surface grid on the keel and the bulb for the T-negative configuration is shown in Figure 20. Triangular cells are used for the discretisation of the surface of the bulb. Special attention has been taken for the discretisation near the wall when generating the volumetric grid. Tetrahedral cells are used for the volumetric grid. Due to the limited computational resources available for this study, the total amount of discretisation cells was always below 500.000. All the simulations are performed using a second-order discretisation scheme (second-order upwind). ResultsâAngle of attack=0Â° The influence of the turbulence model on the value of drag for the configuration T-negative of the âexistingâ bulb is shown in the Table 3. A value of 0.44 N has been measured experimentally. A good agreement is found when using a standard k-Îµ turbulence model (within 2% of the experimental value). Table 3âDrag for the T-negative configuration Drag Angle of attack=0Â° N k-Îµ standard turbulence model 0.430 k-Îµ realizable turbulence model 0.321 Spalart-Allmaras turbulence model 0.363 Using the same turbulence model, the values of drag for the three configurations of the âexistingâ bulb are compared in Table 4. The relative variation of the drag agrees well with the experimental observations, but only the k-Îµ turbulence model gives quantitative data close to the experimental values (within 2%). Table 4âDrag value for the different configurations Numerical Simulation Numerical Simulation Experi. Results k-Îµ std. Spalart-Al. Configuration DragâN DragâN DragâN T-negative 0.430 0.363 0.436 T-positive 0.478 0.380 0.466 Z 0.462 0.376 0.462 ResultsâAngle of attack=6Â° One simulation (configuration T positive) has been performed for an angle of attack of 6Â°, using the standard k-Îµ turbulence model and wall functions. Values of drag and lift are given in Table 5. We observe that the agreement with the experimental values is not as good as for an angle of attack of 0Â°. It should be mentioned that the discretisation is worst than in the previous cases, because the computational domain has doubled (no symmetry plane). An analysis of the sensitivity of the results with the grid size must still be performed for this case. Table 5âlift/dragâangle of attack=6Â° Numerical Simulation Experimental Results Configuration DragâN DragâN the authoritative version for attribution. T-positive 0.54 0.63 LiftâN LiftâN T-positive 2.89 3.5

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 491 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT Contours of static pressure on the bulb and on the keel are shown in Figure 21. The contour of velocity magnitude in a vertical plane located 5 cm behind the tip of the bulb is represented in Figure 22. The deficit of velocity due to the bulb is clearly shown but not the one due to the keel. The velocity map confirms the lower value of drag obtained by numerical simulations. Figure 21âcontours of pressure Figure 22âvelocity magnitude 5 cm behind the tip of the bulb Validation The numerical results for drag and lift generated by the keel are validated with the data obtained using the balance, only when the simulations are performed for no incidence. In these cases, a very good agreement is found when using the k-Îµ standard turbulence model with wall functions. The use of wall function substantially saves computational resources, because the viscosity-affected is not resolved and is well suited for this type of computation. Results with the Spalart- Allmaras, which is specifically designed for aerospace applications, did not agree much with the experimental data, but this is mainly due to the insufficient grid resolution near the wall. Also this model is not performing very well when there is a change in length scale, such as when the flow changes abruptly from a wall-bounded flow to a free shear flow. Simulations performed with an angle of attack of 6Â° have not been validated by the experimental results. Grid is now being modified in order to check the sensitivity of the results with the grid size. Contours of skin friction on the surface of the âexistingâ bulb are validated with the visualization using the surface oil technique. Near the tip of the bulb, the skin friction reaches zero (Figure 23), and this explains the accumulation of oil observed experimentally. As mentioned already before, the shape of the âexistingâ bulb is not an optimal aerodynamic shape. Figure 23âcontours of skin friction CONCLUSIONS Results of a detailed experimental investigation of the aerodynamic performances of two bulbs of different geometry have been presented. Experimental results include visualization of separation zone, the determination of vortex shedding frequencies and the measurement of values of drag and lift for different angles of attack. Two different methods are used for the determination of drag and similar results are obtained. One geometry has also been investigated using numerical simulations with the commercial code FLUENT 5.2. A very good validation is found when computing the drag value for no incidence. This good agreement has only been found when using the standard k-Îµ turbulence model with wall functions. For an angle of attack of 6Â°, the comparison between the experimental and numerical results is not so good. This might be due to the poor grid resolution. Having now more computational resources, the numerical simulations will continue on more refined grids. The ânewâ bulb will also be investigated numerically. the authoritative version for attribution.

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE FLOW AROUND THE APPENDICES OF A WHITBREAD 60 492 lengths, word breaks, heading styles, and other typesetting-specific formatting, however, cannot be retained, and some typographic errors may have been accidentally inserted. Please use the print version of this publication as About this PDF file: This new digital representation of the original work has been recomposed from XML files created from the original paper book, not from the original typesetting files. Page breaks are true to the original; line SAILING YACHT ACKNOWLEDGEMENTS The authors would like to thank the following persons for their help during the experiments or the numerical simulations: F.Helleput, R.De Voghel, T.AndrÃ© and D.Dupont REFERENCES J.Swarbrick: Drawing of WOR 60âprivate communication, 1997 E.N.Tinoco: âIACC Appendages studies', The Eleventh Chesapeake Sailing Yacht Symposium, January 1993 M.Caponnetto: âA review on Il Moro di Venezia Design', The Eleventh Chesapeake Sailing Yacht Symposium, January 1993 A.R.Claughton, R.A.Shenoi, J.F.Wellicome: âSailing Yacht desing: Theory', Addsion Wesley Longman Limited, 333 pages, 1998 J.M.DÃ©lery: âPhysics of Vortical Flows', Journal of Aircraft, Vol. 29, NÂ°5, sept-oct. 1992 S.F.Hoerner: âFluid-Dynamic Drag, Practical information on aerodynamic drag and hydrodynamic resistance', published by the Author, 1958 P.R.Spalart, S.RT.Allmaras: âA one-equation turbulence model for aerodynamic flows', La Recherche AÃ©rospatiale, nÂ°1, 5â21, 1994 L.M.LourenÃ§o: âParticulate image and tracking velocimetry', von Karman Institute Lecture Series, course note 148, 1999 C.A.Marchaj: âAero-hydrodynamics of sailing', Adlard Coles Nautical, 1991 FLUENT 5 User's Guide: Fluent is a registered trademark of Fluent Incorporated GAMBIT User's Guide: Gambit is a registered trademark of Fluent Incorporated the authoritative version for attribution.