Unsteady Sail Dynamics due to Bodyweight motions

2016 ◽  
Author(s):  
Riley R. Schutt ◽  
C. H. K. Williamson

In small sailboats, the bodyweight of the sailor is proportionately large enough to induce significant unsteady dynamics of the boat and sail. Sailors use a variety of techniques to create sail dynamics which can provide an increment in thrust, increasing the boatspeed. In this study, we experimentally investigate the unsteady aerodynamics associated with two such techniques, “upwind leech flicking" and “downwind S-turns". We employ a two-part approach. First, on-the-water experiments are carried out using a Laser class sailboat sailed by Olympic and world championship level sailors. Data collected from an on-board GPS, IMU, anemometer, and camera array is used to generate characteristic motions of the boat and sail relative to the apparent wind. Second, laboratory experiments using the characteristic motion of the sail are run in a computer-controlled 3 degree-of-freedom (X, Y, and θ) towing tank. We use water as the working fluid. Rather than directly experiment with three-dimensional sail shapes, we represent the primary effects of the sail dynamics using rapidly prototyped two-dimensional flexible sail geometries. Shapes are based on extruded draft stripes from the upper third of the sail. The laboratory experiments approximately match the key non-dimensional parameters of the on-the-water sailing conditions, including the reduced frequency and heave-to-chord ratio. Particle Image Velocimetry and force measurements are used to analyze the flow field and thrust generated by the model sail during the dynamic motions. On-the-water testing shows that the characteristic sail motion in leech flicking is a combination of periodic heave caused by the actions of the sailor and a passive twisting of the sail due to rig flexibility. The heaving sail motions are due to rotation (roll) of the rig around the longitudinal axis of the hull. This is at an angle to the apparent wind, resulting in heave that has components both perpendicular and parallel to the oncoming wind flow. This is distinct from classical aerodynamic studies with heave purely perpendicular to the incoming flow. In laboratory experiments, the characteristic flicking motion is applied to a NACA 0012 airfoil and a 2D sail, both angled at 15 deg to the flow. Lift increases and drag decreases, leading to an overall increase in resultant driving force of the boat. The beneficial effect of this dynamic motion becomes greater as the apparent wind angle increases. In the case of leech flicking, the experiments show that the formation of vortex pairs is fundamental to the augmented thrust due to heaving. The presence of S-turns, whereby the sailor changes the boats direction simultaneous with rolling the boat, generally in the downwind direction, is also associated with vortex formation and pairing, which will be described at the conference. During downwind S-turns, large amplitude heaving motions are paired with substantial rotations of the sail caused by both adjustments of the main sheet and changes in heading. Increased velocity made good downwind is measured from the on-the-water experiments, and is associated with an increase of thrust during characteristic dynamics of the airfoil or sail shape in the laboratory.

2018 ◽  
Vol 859 ◽  
pp. 59-88 ◽  
Author(s):  
Philip B. Kirk ◽  
Anya R. Jones

The leading-edge vortex (LEV) is a powerful unsteady flow structure that can result in significant unsteady loads on lifting blades and wings. Using force, surface pressure and flow field measurements, this work represents an experimental campaign to characterize LEV behaviour in sinusoidally surging flows with widely varying amplitudes and frequencies. Additional tests were conducted in reverse flow surge, with kinematics similar to the tangential velocity profile seen by a blade element in recent high-advance-ratio rotor experiments. General results demonstrate the variability of LEV convection properties with reduced frequency, which greatly affected the average lift-to-drag ratio in a cycle. Analysis of surface pressure measurements suggests that LEV convection speed is a function only of the local instantaneous flow velocity. In the rotor-comparison tests, LEVs formed in reverse flow surge were found to convect more quickly than the corresponding reverse flow LEVs that form on a high-advance-ratio rotor, demonstrating that rotary motion has a stabilizing effect on LEVs. The reverse flow surging LEVs were also found to be of comparable strength to those observed on the high-advance-ratio rotor, leading to the conclusion that a surging-wing simplification might provide a suitable basis for low-order models of much more complex three-dimensional flows.


2017 ◽  
Vol 832 ◽  
pp. 697-720 ◽  
Author(s):  
Kyohei Onoue ◽  
Kenneth S. Breuer

We examine the dynamics of the leading-edge vortex (LEV) on a rapidly pitching plate with the aim of elucidating the underlying flow physics that dictates the stability and circulation of the LEV. A wide variety of flow conditions is considered in the present study by systematically varying the leading-edge sweep angle ($\unicode[STIX]{x1D6EC}=0^{\circ }$, $11.3^{\circ }$, $16.7^{\circ }$) and the reduced frequency ($f^{\ast }=0.064{-}0.151$), while keeping the pitching amplitude and the Reynolds number fixed. Tomographic particle image velocimetry is used to characterise the three-dimensional fluid motion inside the vortex core and its relation to the LEV stability and growth. A series of control volume analyses are performed to quantify the relative importance of the vorticity transport phenomena taking place inside the LEV to the overall vortex development. We show that, near the wing apex where tip effects can be neglected, the vortex develops in a nominally two-dimensional manner, despite the presence of inherently three-dimensional vortex dynamics such as vortex stretching and compression. Furthermore, we demonstrate that the vortex formation time and circulation growth are well-described by the principles of optimal vortex formation number, and that the occurrence of vortex shedding is dictated by the relative energetics of the feeding shear layer and the resulting vortex.


2007 ◽  
Vol 581 ◽  
pp. 453-468 ◽  
Author(s):  
MATTHEW J. RINGUETTE ◽  
MICHELE MILANO ◽  
MORTEZA GHARIB

We investigate experimentally the force generated by the unsteady vortex formation of low-aspect-ratio normal flat plates with one end free. The objective of this study is to determine the role of the free end, or tip, vortex. Understanding this simple case provides insight into flapping-wing propulsion, which involves the unsteady motion of low-aspect-ratio appendages. As a simple model of a propulsive half-stroke, we consider a rectangular normal flat plate undergoing a translating start-up motion in a towing tank. Digital particle image velocimetry is used to measure multiple perpendicular sections of the flow velocity and vorticity, in order to correlate vortex circulation with the measured plate force. The three-dimensional wake structure is captured using flow visualization. We show that the tip vortex produces a significant maximum in the plate force. Suppressing its formation results in a force minimum. Comparing plates of aspect ratio six and two, the flow is similar in terms of absolute distance from the tip, but evolves faster for aspect ratio two. The plate drag coefficient increases with decreasing aspect ratio.


1998 ◽  
Vol 122 (1) ◽  
pp. 93-101 ◽  
Author(s):  
D. L. Bell ◽  
L. He

The results of two investigations, concerning the aerodynamic response of a turbine blade oscillating in a three-dimensional bending mode, are presented in this paper. The first is an experimental and computational study, designed to produce detailed three-dimensional test cases for aeroelastic applications and examine the ability of a three-dimensional time-marching Euler method to predict the relevant unsteady aerodynamics. Extensive blade surface unsteady pressure measurements were obtained over a range of reduced frequency from a test facility with clearly defined boundary conditions (Bell and He, 1997, ASME Paper No. 97-GT-105). The test data indicate a significant three-dimensional effect, whereby the amplitude of the unsteady pressure response at different spanwise locations is largely insensitive to the local bending amplitude. The computational results, which are the first to be supported by detailed three-dimensional test data, demonstrate the ability of the inviscid method to capture the three-dimensional behavior exhibited by the experimental measurements and a good level of quantitative agreement is achieved throughout the range of reduced frequency. Additional computational solutions, obtained through application of the strip methodology, reveal inadequacies in the conventional quasi-three-dimensional approach to the prediction of oscillating blade flows. The issue of linearity is also considered, and both experimental and computational results indicate a linear behavior of the unsteady aerodynamics. The second, an experimental investigation, addresses the influence of tip leakage upon the unsteady aerodynamic response of an oscillating turbine blade. Results are provided for three settings of tip clearance. The steady flow measurements show marked increases in the size and strength of the tip leakage vortex for the larger settings of tip clearance and deviations are present in the blade loading toward the tip section. The changes in tip clearance also caused distinct trends in the amplitude of the unsteady pressure at 90 percent span, which are observed to correspond with localized regions where the tip leakage flow had a discernible impact on the steady flow blade loading characteristic. The existence of these trends in the unsteady pressure response warrants further investigation into the influence of tip leakage on the local unsteady flow and aerodynamic damping. [S0889-504X(00)01101-6]


Author(s):  
D. L. Bell ◽  
L. He

The results of two investigations, conducted on the aerodynamic response of a turbine blade oscillating in a three dimensional bending mode, are presented in this paper. The first is an experimental and computational study, designed to produce detailed three dimensional test cases for aeroelastic applications and examine the ability of a 3D time-marching Euler method to predict the relevant unsteady aerodynamics. Extensive blade surface unsteady pressure measurements were obtained for a range of reduced frequency, from a test facility with clearly defined boundary conditions, Bell & He (1997). The test data exhibits a significant three dimensional effect, whereby the amplitude of the unsteady pressure response at different spanwise positions is largely insensitive to the local bending amplitude. The inviscid numerical scheme successfully captured this behaviour, and a good qualitative and quantitative agreement with the test data was achieved for the full range of reduced frequency. In addition, the issue of linearity is addressed and both experimental and numerical tests demonstrate a linear behaviour of the unsteady aerodynamics. The second, an experimental investigation, considers the influence of tip leakage on the unsteady pressure response of an oscillating turbine blade. Results are provided for three tip clearances. The steady flow measurements show marked increases in the size and strength of the tip leakage vortex for the larger tip gaps and deviations in the blade loading towards the tip section. The changes in tip gap also caused distinct trends in the amplitude of the unsteady pressure at 90% span, which were consistent with those observed for steady flow blade loading. It is the authors opinion, that the existence of these trends in unsteady pressure warrants further investigation into the influence of tip leakage upon the local unsteady flow and aerodynamic damping.


2019 ◽  
Vol 213 ◽  
pp. 02072
Author(s):  
Daniil Sergeev ◽  
Alexander Kandaurov ◽  
Olga Ermakova ◽  
Anatoly Suvorov

A series of laboratory and numerical experiments were carried out to study the structure of the turbulent flow over a rectangular obstacle for high Reynolds number. The results of numerical simulation performed within ANSYS CFX were verified on data obtained in the wind tunnel of IAP RAS by visualization methods including Particle Image Velocimetry. It was found that the airflow over the obstacle can be conditionally divided into main several regions: the region of the initiation of the detachment and formation shielding zone, the region of the maximum vertical separation and vortex development and the region of flow reattachment. Comparison of numerical calculations with the results of experiments showed that the physical processes of the airflow around model objects can be optimally modeled in a three-dimensional setting using the Detached Eddy turbulence model (DES) with central numerical differentiation scheme and allowed to select optimal parameters of calculation grid.


2015 ◽  
Vol 766 ◽  
pp. 611-625 ◽  
Author(s):  
Jaime G. Wong ◽  
David E. Rival

AbstractIt is hypothesized that the relative stability of leading-edge vortices (LEVs) on flapping profiles can be improved by moderating LEV growth through spanwise vorticity convection and vortex stretching. Moreover, it is hypothesized that the reduced frequency $k$ and profile sweep ${\it\Lambda}$ are critical in predicting relative LEV stability as determined by the aforementioned effects. These hypotheses are then confirmed experimentally with phase-averaged particle image velocimetry (PIV) and three-dimensional particle tracking velocimetry. In particular, more stable LEVs are observed at higher reduced frequencies, which is argued to represent the ratio between the limiting vortex size and the rate of vorticity feeding. The introduction of profile sweep increased both relative LEV stability and spanwise vorticity transport. It is thought that spanwise vorticity transport improved LEV stability by acting as a sink for vorticity generated in the leading-edge shear layer.


2002 ◽  
Author(s):  
Steven P. O’Halloran ◽  
Mohammad H. Hosni ◽  
B. Terry Beck ◽  
Thomas P. Gielda

Computational fluid dynamics (CFD) simulations were used to predict three-dimensional flow within a one-tenth-scale room. The dimensions of the scaled room were 732 × 488 × 274 mm (28.8 × 19.2 × 10.8 in.) and symmetry was utilized so that only half of the room was modeled. Corresponding measurements were made under isothermal conditions and water was used as the working fluid instead of air. The commercially available software Fluent was used to perform the simulations. Two turbulence models were used: the renormalization group (RNG) k-ε model and the Reynolds-stress model. The CFD setup is presented in this paper, along with the velocity and turbulent kinetic energy results. The simulation results are compared to previously obtained three-dimensional particle image velocimetry (PIV) measurements made within the same scaled room under similar conditions.


Author(s):  
Venkata Ravishankar Kasibhotla ◽  
Danesh Tafti

The paper is concerned with the prediction and analysis of dynamic stall of flow past pitching NACA-0012 airfoil at 105 Reynolds number based on the chord length of the airfoil and at reduced frequency of 0.188 in a three dimensional flow field. The turbulence in the flow field is resolved using large eddy simulations with dynamic Smagorinsky model at the sub grid scale. The lift hysteresis plots indicate closer match to experimental results, although discrepancies exist during the downstroke. The development of dynamic stall vortex, vortex shedding and reattachment as predicted by the present study are discussed in detail. This study has shown that the downstroke phase of the pitching motion is strongly three dimensional and is highly complex, whereas the flow is practically two dimensional during the upstroke.


2013 ◽  
Vol 714 ◽  
pp. 5-23 ◽  
Author(s):  
Daegyoum Kim ◽  
Fazle Hussain ◽  
Morteza Gharib

AbstractVortex formation and force generation of clapping plates with various aspect ratios ($AR$) and stroke angles were investigated. Experiments were performed with a pair of hinged rectangular plates that were rotated symmetrically in a static fluid, and defocusing digital particle image velocimetry was employed to measure the three-dimensional flow field. Single-plate cases were also studied to compare with clapping plate cases. As $AR$ decreases, both circulation of the tip vortex and area enclosed by the vortex loop increase inversely. An empirical power-law relationship with a negative exponent is found between total impulse and $AR$ for a given stroke angle. The sensitivity of the force generated by the plates to the change of $AR$ is larger at the smaller stroke angle because of faster acceleration and deceleration. The increase in impulse per plate from the single-plate case to the clapping double-plate case is larger for lower $AR$. These results reveal that low $AR$ wings are more efficient in propulsive force generation in some specific modes of unsteady flapping flight. The evolution of the wake structures is found to depend on $AR$ and stroke angle.


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