Abstract
The diverse hummingbird family (Trochilidae) has unique adaptations for nectarivory, among which is the ability to sustain hover-feeding. As hummingbirds mainly feed while hovering, it is crucial to maintain this ability throughout the annual cycle—especially during flight-feather moult, in which wing area is reduced. To quantify the aerodynamic characteristics and flow mechanisms of a hummingbird wing throughout the annual cycle, time-accurate aerodynamic loads and flow field measurements were correlated over a dynamically scaled wing model of Anna’s hummingbird (Calypte anna). We present measurements recorded over a model of a complete wing to evaluate the baseline aerodynamic characteristics and flow mechanisms. We found that the vorticity concentration that had developed from the wing’s leading-edge differs from the attached vorticity structure that was typically found over insects’ wings; firstly, it is more elongated along the wing chord, and secondly, it encounters high levels of fluctuations rather than a steady vortex. Lift characteristics resemble those of insects; however, a 20% increase in the lift-to-torque ratio was obtained for the hummingbird wing model. Time-accurate aerodynamic loads were also used to evaluate the time-evolution of the specific power required from the flight muscles, and the overall wingbeat power requirements nicely matched previous studies.
1. Introduction
The Trochilidae is a diverse New World bird family that is highly adapted to nectarivory. A key attribute of hummingbird flight is the ability to sustain hovering for a long period of time, especially during feeding [1,2]. In aerodynamics, hovering is arguably the hardest feat to accomplish as only muscle power is used to support weight [3–5]. The aerodynamic ability to stay airborne while hovering must be preserved throughout the entire annual cycle, including during the energy-demanding period of feather moult, in which wing surface is reduced [6–8]. It is believed that gaps created in the wing during moult may lead to deteriorated aerodynamic capabilities and even failure to hover [9–13]. Therefore, it is important to analyse the aerodynamic loads and the corresponding flow fields throughout the annual cycle, including during flight feather moult, and the ways they may relate to the flyer’s mass and energetics. The present contribution describes our analysis of a complete hummingbird wing. In a second contribution, the same techniques are applied to analyse the aerodynamic loads and flow field over wing models that characterize several flight feather moult stages [14].
Hummingbirds operate at a chord-based Reynolds number (Re) regime of 5000–30 000 [15,16]. While hovering, hummingbirds flap their wings in a nearly horizontal figure eight shape, resembling wing kinematics found in several insect groups [17]. For this reason, it was generally assumed that hummingbirds use similar flow mechanisms as insects, namely, an attached leading-edge vortex [18], despite the large operational Reynolds number difference (insects, Re=10–5000).
In recent years, the ability to analyse flow fields over in vivo natural flyers has altered a few common beliefs about the aerodynamics of hummingbirds. Studies of free-flying hummingbirds have found the lift production to be asymmetric between the stroke-halves, where the power stroke, denoted herein as the downstroke, produces up to 75% of the weight support, contrary to insects where wing support is symmetric [19,20]. Moreover, recent flow measurements have also suggested a relatively small vorticity concentration over the leading-edge of a free-flying rufous hummingbird (Selasphorus rufus, [19,21]). The authors reported that the intensity of this vorticity is highly variable and corresponded to changes between 0.7 and 26% of the total lift production. Similar vorticity concentrations were also measured over the leading-edge of several rotating, dried hummingbird wings at high angles of attack [22].
While large and attached leading-edge vortices characterize the flow field over insect wings (Re<5000 [23–28]), this coherent vorticity structure was reported to break down beyond an operational Reynolds number of 10 000 [29]. Furthermore, Elimelech & Ellington [30] have shown that in a steady rectilinear flow over a hovering hummingbird wing model, the flow was highly unsteady and a transition process was evident even at Reynolds numbers as low as 5000. Such destruction of the leading-edge vortex may strongly diminish the high lift production which is associated with it [29]. Therefore, to better understand how lift is produced, it is of importance to quantify the geometrical extent and the intensity of the vorticity concentration along the hummingbird wing and its characteristics (steady or unsteady).
To meet the tall order of power requirements during hovering, hummingbirds have developed efficient and effective biomechanical systems [3], among which are their flight muscles, comprising 25% of their body mass [31], a value commonly found in flyers with high vertical take-off speed [32]. In hummingbirds, the mass ratio between the supracoracoideus and pectoralis, the flight muscles corresponding to the upstroke and downstroke, is among the highest found in nature [33]. Typically, the supracoracoideus muscle is about one-fifth of the pectoralis mass, but in hummingbirds the ratio is 1 : 2, most likely to allow the upstroke to provide sufficient weight support [3,33].
Estimations of muscle power requirements and wing performance of hummingbirds have been previously studied, mainly by using quasi-steady models [34,35]. These models allow for an indirect estimation of power requirements of free-flying hummingbirds using wing kinematics and morphologies data [4,31,36]. These methods, however, are prone to large uncertainties. Dried hummingbird wings were also tested, mounted on a constantly rotating propeller rig [16,22], allowing experimental repeatability and the ability to accurately preserve wing geometries and surface textures. However, this approach suffers from poor dynamic range measurements as the aerodynamic loads in the air at biologically relevant Reynolds numbers are in the order of a few grams and are consequently difficult to measure. Dynamically scaled planar wings allow for simplification of the mechanical set-up but pose an inherent bias as they do not represent the exact geometry of the wing [16]. In the light of the disadvantages in previously developed experimental methods, in the study presented herein, we investigate the unsteady mechanisms of a three-dimensionally scanned and dynamically scaled Anna’s hummingbird (Calypte anna) wing during the downstroke. By combining high-fidelity, time-accurate aerodynamic loads and flow-field measurements, our aim is to enhance the understanding of the flow mechanisms that develop during the wing’s downstroke and to correlate them to the time-accurate lift, drag and power requirements.
2. Material and methods
2.1. Model wing design and validation
Within the large family of hummingbirds, Anna’s hummingbird is medium-sized; it has an average adult body length of approximately 100 mm, a wing span of 114–121 mm [30] and an average mass of approximately 4.6 g [37]. Anna’s hummingbird flaps its wings, made mostly of 10 primary flight feathers, at a frequency of about 40 Hz (±5% [20,38,39]).
Based on three-dimensional laser scans of a dried, complete male C. anna wing ([30], figure 1a), a 3.5:1, dynamically scaled model wing (figure 1b) was fabricated using stereolithography (Objet VeroBlackTM). Previous studies found that hummingbird wings are rigid, particularly during the downstroke [17,18]. Moreover, scanning electron microscope (SEM) measurements of C. anna’s wing showed a physical connection between neighbouring barbs [30], justifying the use of a rigid and non-porous material for the wing model in our experimental scheme presented below. It is also assumed that wing deformation is minimal [40] and does not play a significant role during the downstroke due to special feather arrangement, as opposed to during upstroke and wing reversal. Therefore, only the downstroke is analysed herein. Regarding wing reversal, there is evidence that it contributes additional circulation generated as the wing rotational velocity decays [19]. However, it is believed that higher fidelity results are required in order to adequately quantify this aspect and consequently it will be the subject of a future study.
Top view of (a) C. anna’s dried wing and (b) a 3.5 : 1 wing model. (c) Schematic illustration of the experimental set-up. The angle of attack, α, is defined as the physical angle between the wing’s root chord and the horizontal plane. (d) Top view of the wing, depicting the coordinate system. (e) The wing motion kinematics, where
2.2. Experimental methods
To investigate the flow over the Anna’s hummingbird wing, time-accurate measurements of the aerodynamic loads acting on the wing, along with flow field measurements using phase-locked particle image velocimetry (PIV), were conducted. The study was carried out using a pair of wings suspended in a tank (0.6×0.6×1 m) filled with a working fluid (figure 1c) that varied between the two sets of experimental set-ups to meet the aerodynamic similarity constraints and their inherent limitations. A controller unit (Technosoft IPOS3604-VX-CAN, Neuchâtel, Switzerland) controlled a servomotor (3257CR32A, Faulhaber, Schönaich, Germany) which rotated the wing pair around a vertical axis (figure 1c). Each wing followed stages of initial acceleration, steady rotation and deceleration to model the downstroke of a flapping wing (figure 1e). The motion command was subjected to the kinematical constraint of approaching mid-downstroke, where θ=90°, at the middle of each wing cycle (θ denotes the wing’s angular position, figure 1d). These simplifications allowed us to coherently analyse the basic flow mechanisms that developed over the wing at one distinct Reynolds number, avoiding second-order effects. In this study, Re=10 000 and is defined as
Experimental dimensional data: ρ is the working fluid’s specific weight; ν is the working fluid’s kinematic viscosity; T is the duration of each experimental repetition; f is the flapping frequency;
2.3. Aerodynamic load measurements
Measuring time-accurate aerodynamic loads at Reynolds numbers of several tens of thousands and below is challenging, because the variation in physical loads can be subtle, requiring a highly sensitive measuring system. Moreover, resolving the time development of the aerodynamic loads requires a reliable mechanical system and high speed data acquisition tools due to the high frequency of the flapping wings. Using dynamic similarity rules, the aerodynamic loads were measured in water–glycerine solutions rather than in air. The 3.5:1 dynamically scaled wing model, together with the high specific weight of the working fluid (water–glycerine) and its viscosity (table 1), allowed for the obtainment of a biologically relevant Reynolds number of 10 000 at a revolving frequency which was in the order of 1 Hz (table 1). In these conditions, the dimensional aerodynamic loads were about five times higher than those that would have been obtained in air, achieving a wider dynamic range for the load measurements.
The entire mechanical assembly of the flapper was mounted on a six-component force and moment transducer (MINI40, calibration SI-20-1 by ATI Industrial Automation, Apex, NC, USA) that recorded the aerodynamic loads acting on the wings (figure 1c). The transducer’s dynamic range was 60 N in lift and 1 Nm in torque. A real-time control unit (National Instruments cRIO-9022, Austin, TX, USA) was used to sample the transducer’s analogue signals, which were recorded simultaneously at 10 kHz. The aerodynamic lift, L, and torque due to drag, Q, of one wing are referenced to
Top and side views of the experimental schemes that recorded the flow over the wing at α=30°: (a,b) stations along the span; (c,d) in the near-wake area behind the wing.
The time-averaged aerodynamic coefficient for each individual load measurement i (1≤i≤n), is defined as
2.4. Flow field measurements
Two schemes of flow field measurements were applied in order to analyse the flow field over the printed model wing at constant span stations (figure 2a,b) and behind the wing in the near-wake section (figure 2c,d). Following the first scheme, to investigate the flow over the wing root, middle and tip, the in-plane velocity field was recorded at z=r/R=0.25, 0.5 and 0.75 (figure 1d). For better image quality, the flapping frequency was reduced relative to the aerodynamic loads measurements, and therefore, due to similarity constraints, the wing pair was tested in pure water (table 1). In order to analyse the high lift flow mechanisms developing along the downstroke of a hummingbird wing, we focused our efforts to acquire high-fidelity flow field measurements at a single, relatively high, biologically relevant angle of attack, α=30° [17,21,22,41,42] (for further explanation as to why this angle of attack was chosen see Results, Flow field section below). The flow fields were acquired using a PIV system (Dantec Dynamics A/S, Skovlunde, Denmark). It consisted of a dual-cavity 30 mJ Nd:YLF laser with a repetition rate of up to 10 Hz, a 4M pixel resolution 12-bit CCD camera (FlowSense EO) and a programmable timing unit. The laser-head was mounted on a platform at the front of the water tank (figure 2b,d). A cylindrical lens was used to create a thin light sheet of approximately 2 mm in thickness, and the double exposure camera equipped with a 50 mm lens was mounted on a tripod perpendicular to the laser sheet. This set-up yielded a maximal field of view of approximately 210×156 mm, capturing the flow behind the wing along the entire wing span, as shown in figure 2c,d. Silver-coated, hollowed, glass spheres with a mean diameter of 10 μm (Dantec Dynamics A/S, Skovlunde, Denmark) were used as seeding particles.
During each wing motion, high-speed image sequences were recorded at several angular wing positions throughout the motion. Using an optical switch (YH03NCT8, Wenglor, Tettnang, Germany), a synchronization pulse was fired to the camera and laser-head at these specific angular positions. In order to keep the same camera calibration and illumination settings, the initial angular position of the wing was modified to allow for image capturing at a fixed position with respect to the camera. To improve the signal-to-noise ratio, each test condition was repeated 50–80 times. Similar to the acquisition of the aerodynamic loads, the wing was paused at the end of each wing downstroke in order to establish an essentially quiescent flow at the beginning of each successive measurement. The PIV processing was conducted using DynamicStudio v. 3.4.1 (Dantec Dynamics A/S, Skovlunde, Denmark). The two-dimensional PIV procedure yielded two in-plane velocity components, which were computed from the cross-correlation of pairs of successive images with 50% overlap between the interrogation domains. The seeding density allowed for high-quality vector fields with interrogation windows of 32×32 pixels (spatial resolution of approx. 1.6 mm).
The dimensional unsteady velocity field is denoted as
3. Results
3.1. Aerodynamic loads
The time-dependent development of the aerodynamic coefficients, CL and CQ, is presented in figure 3a,b, respectively, for various angles of attack. The standard deviation (s.d.) of the aerodynamic load measurements is represented by the shaded region on top of the mean value for each one of the cases. At α≤20°, lift levels increased monotonically along with the angle of attack, while, at α≥25°, lift production reached saturation. Interestingly, unlike the lift production over rotating wings at low Reynolds numbers [26], the lift coefficient did not reach a steady state during the downstroke (figure 3a). Two oscillatory patterns were measured; pattern 1 corresponding to 5°≤α≤15°, where damped oscillations appear, and pattern 2 at 20°≤α≤35°, where oscillations of higher frequency persist throughout most of the downstroke. This phenomenon will be further discussed below. Unlike CL’s development along the downstroke, the results show a distinct correlation between the torque coefficient, CQ, and the angular velocity profile (figure 3b).
Time-accurate aerodynamic coefficients along the downstroke at all tested angles of attack: (a) lift (b) torque due to drag. Solid lines denote ensemble-averaged values; shaded regions represent the standard deviation (s.d.) value at each angular position. The dashed line in (b) represents the wing angular velocity profile along the downstroke. (c) Time-averaged aerodynamic coefficients at different angles of attack. Error bars represent the time-averaged standard deviation of measurements, magnified five times, for clarity. (d) Lift-to-torque ratio, compared to Polhamus leading-edge vortex geometric model of
The time-accurate development of the aerodynamic loads was time-averaged in order to efficiently quantify all of the aerodynamic characteristics of the downstroke (as presented in equations (2.2) and (2.3)). The time-averaged aerodynamic coefficients,
3.2. Flow field
The flow fields over the C. anna’s wing model were acquired at α=30°. Such angle is at the higher end of hummingbirds’ operational angles of attack [17,21,22,41,42]. This allowed us to analyse coherent flow features over the wing, and qualitatively relate the flow fields to lower angles according to pattern 2 (as low as α=20°, figure 3a).
Representative flow fields for several angular wing positions along the downstroke are presented in figure 4. The dimensionless magnitude of the in-plane velocity,
Flow field development at stages throughout the downstroke at α=30°. Rows are arranged by ascending span location: (a–c) z=0.25, (d–f) z=0.5 and (g–i) z=0.75. Columns are arranged by ascending angular position: θ=10° (a,d,g), θ=90° (b,e,h) and θ=170° (c,f,i). The colour scheme describes the in-plane velocity magnitude. Column (b,e,h) depicts the streamlines over the wing. The solid black line depicts the wing’s position, and the shaded grey area is the illumination shadow region behind it.
The lift-to-drag ratio was previously used to assess whether a leading-edge vortex mechanism is present [43]. In such scenarios, the flow separates from a sharp leading-edge, causing elimination of or a severe drop in leading-edge suction. This yields a net force which is normal to the wing surface, and therefore, a geometric relation between lift and drag forces, where
One of the flow quantities associated with upward (or, positive) lift is the effective disc area. This area is denoted by a region of downward (or negative) vertical velocity, v (background colour in figure 5a,d,g). In these figures, the effective discs of representative stages along the downstroke are referenced to the wing disc area (Sd=π[(R+Rη)2−(Rη)2]). At θ=22.5°, the effective disc area is restricted by two coherent vortices, one at the wing root and one at its tip (figure 5a,b), similar to vortices observed in in vivo flow field measurements [20]. Seventy-eight per cent of the wing disc at this stage contributed to the effective disc area (figure 5a), while at later stages this area shrank to 65% at θ=45° (figure 5d) and 50% at θ=90° (figure 5g). At mid-downstroke, the wing tip vortex broke down. This phenomenon is described by the growing flow fluctuations within that flow region (figure 5h). This vortex breakdown started in the vicinity of the wing tip and progressed towards the medial portion of the wing, as it reached z=0.5 at θ=45° (figure 5e) and z=0.25 at θ=90° (figure 5h).
Near-wake flow fields measured at α=30°. Rows are arranged by ascending angular position: (a–c) θ=22.5°; (d–f) θ=45°; (g–i) θ=90°. Column (a,d,¡textit¿g¡/textit¿) depicts the near-wake flow field. The colour scheme denotes the ensemble averaged vertical velocity component, v; the flow fields standard deviation, σvw, is presented in column (b,e,h). Wing contour and the measured span stations are shown for reference; the flow fields at z=0.75 are presented in column (c,f,i); see figure 4 for panel descriptions.
4. Discussion
4.1. Survival of the leading-edge vortex
The lift-to-torque ratio, which is proportional to
Vorticity contours measured at α=30° over the wing depicting the spanwise vorticity concentration development at (a) θ=22.5°, (b) θ=90° and (c) θ=157.5°. A magnification of the tangential flow field in the vicinity of the leading-edge is presented for the distal span station (z=0.75) in (b), where the red line denotes the inflection points. (d) Net circulation; (e) positive and negative circulation. Circulation distribution along the span (scattered dots), corresponding to Ellington’s dynamic stall model [35] at (f) θ=10°, (g) θ=90° and (h) θ=170°. The model was scaled to produce the same integrated circulation along the span as the measured circulation.
The spanwise vorticity structure presented above differs from the leading-edge vortex associated with flow over wings at considerably lower Reynolds numbers [24,25,28,46]. At characteristic Reynolds numbers of several hundred, the leading-edge vortex is almost circular (aspect ratio of about 1) and extends over about half of the local wing chord [24,25,28]. The present results from C. anna wings show that the spanwise vorticity structure covers a maximum of about one-third of the local chord length at mid-span and θ=157.5° with an aspect ratio ranging between 8 and 3.3 at the root and medial span stations, respectively (figure 6c). The structure of the spanwise vorticity concentration, found over the leading-edge, is similar to that previously found over rufous hummingbirds [19]. Moreover, the flow fluctuation levels within the spanwise vorticity structure over the wings of Anna’s hummingbird are considerably higher than those over insect wings, as in the latter, the leading-edge vortex was found to remain steady (essentially zero flow fluctuations).
In order to quantify the contribution of the leading-edge spanwise vorticity to the wing lift, the dimensionless circulation was calculated by integrating the dimensionless vorticity fields [46]. The development of the net circulation (Γ) over the three measured span-stations is presented in figure 6d. During wing acceleration (θ<22.5°), high circulation growth rates were measured. As reported before [46], this phenomenon can be explained by the low vorticity convection towards the wing tip, because spanwise velocity has not developed considerably at this stage of the downstroke. Later on, spanwise velocity grows, causing the accumulated vorticity to convect towards the tip and slow down the circulation growth rate (figure 6d).
At the end of the acceleration stage (22.5°<θ<45°), the net circulation over the distal span station (z=0.75) abruptly dropped, as marked by the dashed line in figure 6d. To better explain this phenomenon, the net circulation was decomposed into its positive (spanwise), Γ+, and negative, Γ− parts (see figure 6e). Naturally, Γ+ is associated with spanwise vorticity production over the leading-edge. Γ− and its characteristically high standard deviation are associated with flow fluctuations. It is apparent that the large detached flow region in the vicinity of the wing tip induced high values of negative circulation resulting in the abrupt drop in net circulation (figure 6d). At mid-downstroke (θ=90°), flow field measurements over the mid-span of the wing (z=0.5) have also suggested the development of a large detached flow area forming behind the leading-edge vorticity structure (figure 4e). It is noteworthy that despite the abrupt growth of the negative circulation (in magnitude), as presented for θ=45°, the net circulation kept its monotonic growth until the wing reached θ=135° (figure 6d). This outcome emphasizes the significance of the vorticity structure forming over the leading-edge and the strength of the positive circulation (Γ+) in that area.
By referring to previous studies’ circulation measurements and specifically to their corresponding wing tip velocities and chord lengths, comparisons can be made to the dimensionless circulation presented in figure 6d,e. Good agreement to similar in vivo dimensionless flow field measurements of a rufous hummingbird is evident, which may suggest a similar vorticity mechanism under natural free-flight settings [19]. Interestingly, dimensionless circulation values are also similar to those measured over insect wing models at different Reynolds regimes, suggesting that the vorticity concentration found over the wing model of C. anna performs similarly to an attached leading-edge vortex [47]. This similarity encouraged us to compare the presented results to Ellington’s dynamic stall model (figure 5f–h), which was originally formulated in order to quantify the leading-edge vortex that formed over insect wings at Reynolds numbers between a hundred and a few thousand [35]. It suggests that circulation associated with upwards lift, Γ+, is proportional to zc, where z is the spanwise location and c is the corresponding wing chord length. For each stage along the downstroke, a proportional scale factor was set such that the measured circulation matched that of the model in order to analyse its distribution along the span. Applying this model to Γ+ in the presented analysis showed a remarkable match, suggesting that the spanwise vorticity concentration over C. anna’s wings yields positive circulation, similar to the one that developed over wings of much lower Reynolds numbers. However, the net circulation was not comparable to Ellington’s dynamic stall model. Therefore, the presented spanwise vorticity structure that was measured over the wings of C. anna will be hereafter dubbed a leading-edge bubble.
4.2. Flow structures
During the downstroke, the flow field over C. anna’s wings, as was already shown above, is highly unsteady (figure 5). Flow fluctuation levels over the wing at different span stations reached values as high as σuv=0.7 (figure 7). At wing stations where the flow is mostly attached to the wing (i.e, z=0.5, and θ=45°, figure 7a), high standard deviation values are mostly constrained within the leading-edge bubble. Detached flow regions are characterized by high values of flow fluctuations (figure 7b–d), but these are not restricted only to the vicinity of the leading-edge. Interestingly, the lift standard deviation at α=30°, matched the standard deviation of the integral of net circulation (Γ) along the span, stressing the relation between lift and net circulation and not only to that which originated from Γ+.
Flow field standard deviation, σuv, at representative span stations and angular positions along the downstroke, measured at α=30°: (a) z=0.5, θ=45°; (b) z=0.5, θ=90°; (c) z=0.75, θ=45°; (d) z=0.75, θ=90°.
The time-accurate load measurements indicate a certain frequency which is dominant during the downstroke (figure 8a). The typical dimensionless frequency of these undulations (Strouhal number) is St=0.98, where
Modal inspection of the flow fields, measured at α=30°, and links to aerodynamic forces. (a) CL at α=30°. The spanwise vorticity fields of the two strongest modes (referenced to the highest vorticity value) at representative span stations and angular position along the downstroke: (b,c) z=0.75 and θ=45°; (d,e) z=0.5 and θ=90°. λ is the structure shedding wavelength.
As POD does not yield the respective frequency of the dominant spatial modes, these were estimated using the wavelength as the appropriate length scale and the convective velocity between two adjacent vorticity concentrations. At θ=45° and z=0.75 (figure 8b,c), this analysis yields a dimensionless frequency of St=0.91, in good agreement with the dimensionless frequency that characterized the direct lift measurement (St=0.98, figure 8a). This suggests that these flow fluctuations originated from the vorticity concentrations which were shed from the leading-edge bubble further downstream. At θ=90° and onwards, more frequencies are evident (figure 8a); indeed, at z=0.5, the dominant Strouhal number in the flow field is St=0.67 (figure 8d,e). It is likely that this diversity of frequencies is due to different sheer layer thicknesses and convective velocities at each spanwise station; however, this should be confirmed in a dedicated study.
4.3. Hovering performance
Hovering is a demanding type of flight as weight support is solely a function of the flight muscles’ capabilities. To assess the effects of the oscillating aerodynamic loads and flow fluctuations on wing performance, the downstroke time-averaged aerodynamic coefficients were used to estimate the entire wingbeat (downstroke and upstroke) aerodynamic characteristics during hovering. The required time-averaged lift coefficient (given per wing) to support the bird’s body weight is
Flow field measurements indicate that 66% [19,20,52] to 75% [21] of weight support is provided by the downstroke motion of the C. anna wing. Therefore, the entire natural wingbeat time-averaged lift (
where h is a proportional factor accounting for the downstroke contribution to the overall wingbeat lift production (0.66≤h≤0.75). A sensitivity analysis showed that the presented
In order to assess the biological conditions in which Anna’s hummingbirds hover, aerodynamic lift is required to support the bird’s weight; therefore,
A key factor enabling hummingbirds to sustain hovering flight is their flight muscle power output. The power factor (
Performance characteristics of C. anna’s wing. (a)
We use our dimensionless results in order to estimate C. anna’s dimensional energetics. The hovering muscles’ aerodynamic power output during the downstroke, P, was calculated (multiplied by 2 to refer to a wing pair) using the time-accurate aerodynamic torque due to drag (CQ):
Our experimental calculation suggests that
Since each wing is accelerated and decelerated along the downstroke, flight muscles must overcome varying power requirements which may be higher than the time-averaged one. Using the time-accurate aerodynamic load measurements, the varying specific power (P*) along the downstroke is presented in figure 9b for
5. Conclusion
This study is part of our effort to analyse the aerodynamic characteristics of the flapping wing of C. anna throughout its annual cycle. In the present contribution, we concentrated on the baseline wing configuration while laying the foundations of our analysis techniques that will be used to address the flow mechanisms and aerodynamic characteristics of several wing geometries that characterize several stages of the wing moult cycle [14]. The flow field over the wing revealed unsteady spanwise vorticity concentrations that are formed and shed in the vicinity of the leading-edge. Because this spanwise vorticity formation has some similarities to the leading-edge vortex that was found over flapping wings at much lower Reynolds numbers, this phenomenon is dubbed the leading-edge bubble. In this bubble, the flow separates and creates a low pressure region, similar to the one that evolved within the leading-edge vortex. The difference between the two is that in the former, vortex shedding evolves too, introducing more time scales to this flow field (or more frequencies). As this evolution does not reach a steady state (like the one over a steady translating wing), the aerodynamic characteristics remain fruitful (i.e. high enough lift-to-torque ratio and notable lift). At the end of stroke, these vorticity concentrations are being convected thanks to the down-wash and a new leading-edge bubble is being created. The unsteady nature of the leading-edge bubble was revealed by the time-accurate load measurements and nicely matched the detailed spatial analysis of the flow field.
The high fidelity and time-accurate results are in good agreement with power requirements estimated from free-flying hummingbirds. Furthermore, the presented approach allows a detailed and direct investigation of hummingbird wing performance; this approach can be used to further investigate more aspects of the highly complex aerodynamics of hummingbirds and the associated flow mechanisms such as wing reversal and the upstroke of deformed wings.
Data accessibility
All data underlying this publication are available via Dryad http://dx.doi.org/10.5061/dryad.mr556 [57].
Authors' contributions
Y.A, Y.E. and N.S. designed the experiments and wrote the paper. Y.A. and Y.E. performed data gathering and analysis.
Competing interests
We declare we have no competing interests.
Funding
We received no funding for this study.
Acknowledgements
We thank ATS, Applied Technologic Services, LTD (Herzelia, Israel) for providing the PIV system. We also thank Ms Dorin Avsaid, Mr Noam Neeman and Mr Roei Elfassy for their help obtaining the PIV data. We acknowledge Distinguished Professor Emeritus Daniel Weihs for his insightful remarks.
Appendix A
A.1. Aerodynamic coefficients calculation
The measured vertical force (Fy, positive upwards) measured by the force and moments transducer is the sum of the following forces acting on one wing:
The aerodynamic torque, denoted as Q, is the torque because drag is acting on the wing. To distinguish the aerodynamic torque, Q, from the overall torque measured by the force and moments transducer around the vertical axis (see free-body diagram of the experimental set-up in figure 10), the equation system without external torques is as follows:
The schematic of the mechanical system. D is the drag force acting on the wing.
- Received March 9, 2017.
- Accepted July 24, 2017.
- © 2017 The Authors.
Published by the Royal Society under the terms of the Creative Commons Attribution License http://creativecommons.org/licenses/by/4.0/, which permits unrestricted use, provided the original author and source are credited.