control of wing vortices
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R. King (Ed.): Active Flow Control, NNFM 95, pp. 137151, 2007.
springerlink.com Springer-Verlag Berlin Heidelberg 2007
Control of Wing Vortices
I. Gursul, E. Vardaki, P. Margaris, and Z. Wang
Department of Mechanical Engineering
University of Bath
Bath, BA2 7AY, United Kingdom
Summary
Vortex control concepts employed for slender, nonslender and high aspect ratio wings
were reviewed. For slender delta wings, control of vortex breakdown has been the
most important objective, which is achieved by modifications to swirl level and
pressure gradient. Delay of vortex breakdown with the use of control surfaces,
blowing, suction, high-frequency and low-frequency excitation, and feedback control
was reviewed. For nonslender delta wings, flow reattachment is the most important
aspect for flow control methods. For high aspect ratio wings, vortex control concepts
are diverse, ranging from drag reduction to attenuation of wake hazard and noise,
which can be achieved by modifications to the vortex location, strength, and structure,
and generation of multiple vortices.
1 Introduction
Controlling vortical flows over wings may have various benefits, such as
enhancement of lift force, generation of forces and moments for flight control,
attenuation of buffeting, reduction of drag, and attenuation of noise due to
vortex/blade interaction. Control methods include manipulation of one or more of the
following flow phenomena: flow separation from the wing, separated shear layer,
vortex formation, flow reattachment on the wing surface, and vortex breakdown. The
occurrence and relative importance of these phenomena strongly depend on the wing
sweep angle.For delta wings, flow reattachment and vortex breakdown are two important
phenomena, which determine the effective flow control strategies. The reattachment
location on the wing surface moves inboard with increasing angle of attack, and
reaches the wing centreline at a particular incidence. Beyond this limiting angle of
attack FR, flow reattachment to the wing surface is not possible. The variation of
predictions [1] ofFR with wing sweep angle is shown in Figure 1. This prediction is
only valid for slender wings, and the only experimental observation [2] for a
nonslender wing (by visualization of the reattachment line for a sweep angle of
=50) is also given in Figure 1. For slender wings, it is seen that the reattachmentincidence decreases with increasing wing sweep angle. Therefore, on highly swept
wings, reattachment does not occur beyond small angles of attack.
Vortex breakdown appears on the wing with increasing angle of attack and crosses
the trailing-edge at a particular incidence BD. The variation of this angle of attack
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138 I. Gursul et al.
[3] with wing sweep angle is also shown in Figure 1. It is seen that this angle of
attack increases with increasing wing sweep angle. On nonslender wings, vortex
breakdown appears at very small incidences.
As the vortex control concepts become increasingly diverse, new actuators and
closed-loop control strategies are being developed. It is useful to consider the flowphysics and dominant mechanisms as these determine which flow control methods are
effective. The main objective of this paper is to review the vortex control concepts,
which mainly depend on the wing sweep.
WING SWEEP [deg]
ANGLEOFATTACK
[deg
]
45 50 55 60 65 70 75 80 850
10
20
30
40
VORTEX
BREA
KDOW
N
NOBREAKD
OWN
NOREATTACHMENT
REATTACHMENT
Fig. 1. Boundaries of vortex breakdown and flow reattachment on the wing surface as a
function of sweep angle
2 Slender Delta Wings
2.1 Overview of Flow Physics
The flow over a delta wing is characterised by a pair of counter-rotating leading-edge
vortices that are formed by the roll-up of vortex sheets. The time-averaged axial
velocity is jet-like at low and moderate incidences. The large axial velocities in the
vortex core are due to very low pressures, which also generate additional suction andlift force, known as vortex lift, on the delta wings. Vortex lift contribution increases
with wing sweep angle [4].
At a sufficiently high angle of attack, the vortices undergo a sudden expansion
known as vortex breakdown. The axial flow downstream becomes wake-like with
very low velocities. For slender wings (defined as 65 in this paper), vortex
breakdown is the dominant flow mechanism that is responsible for decreased lift. It is
also the dominant source of unsteadiness that causes wing and fin buffeting [5].
Hence control of vortex breakdown has been the subject of many investigations [6].
There are two important parameters affecting the occurrence and movement ofvortex breakdown: swirl level and pressure gradientaffecting the vortex core. An
increase in the magnitude of either parameter promotes the earlier occurrence of
breakdown. Very early experiments [7] demonstrated that vortex breakdown moves
upstream over delta wings when the magnitude of either parameter is increased.
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Control of Wing Vortices 139
More recently, it was shown [8] that the minimum swirl level required for breakdown
decrease with increasing magnitude of adverse pressure gradient. Naturally, flow
control methods for the delay of vortex breakdown rely on modification of these two
parameters.
Active flow control methods generally rely on unsteady excitation in flow controlapplications. Unsteady forcing has been used for the control of vortex and breakdown
in some cases. There are various sources of unsteadiness [5]: shear layer instabilities,
vortex wandering, helical mode instability of vortex breakdown, oscillations of
breakdown, vortex interaction, and vortex shedding. The frequency spectrum of the
unsteady flow phenomena that exist over stationary wings is very wide, which is one
of the challenges in numerical simulations of these flows. Vortex breakdown, vortex
interactions, and vortex shedding, either alone or in combination, play an important
role in wing and fin buffeting, although vortex breakdown is the main source of
buffeting over slender wings. Flow control approaches for vortex breakdown arereviewed next.
2.2 Control Surfaces
Various control surfaces [6] have been investigated to control the formation, location,
strength, and breakdown of the leading-edge vortices: canards, strakes, leading-edge
flaps, apex flap, and variable-sweep wings. It is well known that canards can provide
substantial delays [9] in vortex breakdown by affecting the external pressure gradient
acting on the vortex core.
Since all of the vorticity of leading-edge vortices originates from the separationpoint along the leading-edge, leading-edge flaps are particularly attractive tools that
can be used to influence the strength and structure of these vortices. Leading-edge
flaps that are deflected downward have been found to reduce drag and improve the
lift-to-drag ratio [10]. On the other hand, the flap deflection in the upward direction
causes an increase in lift as well as drag. This type of vortex management can be
used for landing or aerodynamic manoeuvres [10]. It has been found that the flaps
deflected upward generate a stronger vortex lift at low and moderate angles of attack.
However, flaps may also induce vortex breakdown [11]. Leading-edge flaps modify
the strength and location of the vortices, thereby affecting the parameters that controlvortex breakdown. It was shown [11] that breakdown location and its sensitivity
strongly depend on incidence and flap angle. For large angles of attack, the variation
of breakdown location is not monotonic, and therefore, not suitable for control
purposes.
A variable leading-edge extension [12] that effectively varies the sweep angle has
been used to control leading-edge vortices and breakdown. The advantage of this
method is that the variation of breakdown with sweep angle is monotonic, hence
suitable for active control purposes. Because most of the vorticity within the vortex
core originates from a small region near the apex of the wing, an apex flap can be aneffective control surface. It was shown [13] that a drooping apex flap could delay
vortex breakdown.
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140 I. Gursul et al.
2.3 Blowing and Suction
Blowing and suction applied at various locations are commonly used as flow control
methods for leading-edge vortices and breakdown. The most widely used versions
include: (a) leading-edge suction/blowing, (b) trailing-edge blowing, (c) along-the-core blowing. These are discussed in detail below.
Since the vorticity of the leading-edge vortices originates from the separation line
along the leading-edge, control of separation characteristics or shear layer can be used
to influence the strength and location of the vortices as well as the location of vortex
breakdown. Steady blowing [14, 15] and suction [15, 16] at the leading-edgehas
been employed, but these methods differ in terms of their effect on swirl level. While
blowing, in particular tangential blowing, may increase the swirl level, suction
reduces the strength and swirl level due to removal of some of the vorticity shed from
the leading-edge. Figure 2(a) shows how the location of shear layer and vortex is
modified upstream of breakdown when suction is applied. Figure 2(b) shows theaxial velocity contours at the trailing-edge, which show the change from wake-like to
jet-like velocity as a result of the delay of vortex breakdown. Detailed measurements
[16] show that maximum swirl angle in the core and circulation decrease with suction,
which causes the vortex breakdown location to move downstream. It is also worth
noting that the leading-edge suction technique does not require thick rounded leading
edges. Control of vortices can be achieved without the use of the Coanda jet effect.
Fig. 2. Variation of (a) rms axial velocity upstream of breakdown location; (b) time-averaged
axial velocity at x/c = 1.0
The effect of trailing-edge jets on wing vortices and vortex breakdown has been
investigated in several studies [17-20]. Blowing at the trailing-edge also modifies the
external pressure gradient and causes delay of vortex breakdown. Favourable effect
of a trailing-edge jet [17] could be observed even in the presence of a fin, which
produces a strong adverse pressure gradient for a leading-edge vortex. It was shown
that fin-induced vortex breakdown can be delayed even for the head-on collision of
the leading-edge vortex with the fin [19]. Hence the adverse pressure gradient caused
by the presence of the fin could be overcome with a trailing-edge jet. The
(b)(a)
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Control of Wing Vortices 141
effectiveness of a trailing-edge depends on the wing sweep angle [20]. It appears that
it becomes more difficult to delay vortex breakdown with decreasing sweep angle.
Along-the-core blowing [21, 22] accelerates the axial flow in the core, and
modifies the pressure gradient favourably. Figure 3 shows the effectiveness of
various blowing/suction methods from various studies published in the literature.Here the effectiveness is defined as (xbd/c)/C, where xbd is the change in
breakdown location (positive corresponding to delay), c is the chord length and C is
the momentum coefficient. Figure 3 shows that along-the-core blowing is the most
effective method in terms of delaying vortex breakdown. This can be attributed to the
importance of the pressure gradient affecting the vortex core. It is also seen that the
effectiveness of blowing and suction is nearly the same. The effectiveness of trailing-
edge blowing is the lowest among all blowing methods considered.
10-2
10-1
100
101
102
Along-the-core blowing
Leading-edge suction/blowing
Trailing-edge blowing
Xbd/c
C
Fig. 3. Effectiveness of various blowing/suction methods from several studies published in the
literature
2.4 Unsteady Control
There have been various attempts to control vortices and breakdown by using
unsteady excitation. These include small and large amplitude oscillations of leading-edge flaps, periodic variations of sweep angle, periodic suction or blowing, and
combined use of leading-edge flaps and intermittent trailing-edge blowing, which are
summarized in Reference [5]. These studies fall into two categories: (i) high-
frequency excitation, St = fc/U = O(1), (where f is the frequency and U is the free
stream velocity) and (ii) low-frequency excitation, St = O(0.1).
For the high-frequency excitation, Gad-el-Hak and Blackwelder [23] applied
periodic perturbations of injection and suction along the leading-edge of a delta wing
( = 60). They found maximum changes in the evolution of the shear layer when thefrequency of perturbations (St = 5.5) is the subharmonic of the frequency of Kelvin-
Helmholtz instability. However, no results were reported regarding the structure ofthe main vortex and the effect on vortex breakdown. Gu et al. [24] applied periodic
suction-blowing in the tangential direction along the leading-edge of the wing ( =
75) and reported a delay of vortex breakdown. The most effective period of the
alternate suction-blowing corresponded to fc/U = 1.3. For a less slender wing
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142 I. Gursul et al.
( = 60), it was shown that oscillatory blowing at the leading edge can enhance thelift at high angles of attack [25], and optimum reduced frequency varied in the range
of fc/U = 1 to 2. For small amplitude flap oscillations, the strength of the vortices
was larger than that of the quasi-steady case [26], when the excitation frequency was
St = 1.2. This range of effective frequencies presumably corresponds to subharmonicsof the Kelvin-Helmholtz instability due to vortex pairing.
For the low-frequency excitation, there have been reports [5] of increased vortex
circulation and delay of vortex breakdown for oscillating flaps, delay of vortex
breakdown for harmonic variations of sweep angle for a variable sweep wing, and
delay of breakdown for combined flaps and unsteady trailing-edge blowing. When
the spectra of unsteady flow phenomena [5] are considered, it is less clear which
unsteady phenomena are exploited for the low-frequency excitation. However, it is
suggested [27] that the variations in the external pressure gradient generated by
unsteady excitation plays a major role.
2.5 Feedback Control
The pressure fluctuations induced by the helical mode instability of vortex breakdown
can be measured and used as a feedback signal for active control. In such a approach,
the rms value of pressure is chosen as the control variable and a feedback control
strategy is considered [28]. The monotonic variation of the amplitude of the pressure
fluctuations with vortex breakdown location makes the feedback control possible.
In identifying a suitable flow controller, several methods were considered,
including blowing, suction, and flaps. However, the relationship between the vortexbreakdown location and control parameter is unknown or undesirable (i.e., not
monotonic) for these methods. A desirable controller should have a monotonic
relationship between the control parameter and breakdown location. It was shown
[28] that it was feasible to use a variable sweep angle mechanism as a means of
controlling the breakdown location by influencing the circulation of the leading-edge
vortex. The system was idealized as a first-order system, and integral control was
used. The feedback control of breakdown was demonstrated for stationary as well as
pitching delta wings.
3 Nonslender Delta Wings
3.1 Overview of Flow Physics
Vortical flow over nonslender delta wings ( 55) has recently become a topic of
increased interest in the literature. While the flow topology over more slender wings,
typically 65, has been extensively studied and is now reasonably wellunderstood, the flow over lower sweep wings has only recently attracted more
attention [29]. Vortical flows develop at very low angles of attack, and form close to
the wing surface. One of the distinct features of nonslender wings is that
reattachment of the separated flow is possible even after breakdown reaches the apex
of the wing. However, at large angles of attack in the post-stall region, reattachment
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Control of Wing Vortices 143
is not possible, and completely stalled flow occurs on the wing. Active and passive
control of reattachment may be beneficial for lift enhancement in the post-stall region.
According to Polhamus leading-edge suction analogy [4], the vortex lift
contribution becomes a smaller portion of the total lift as the sweep angle decreases.
Vortex breakdown occurs over the wing even at small incidences, and there is noobvious correlation between the onset of vortex breakdown over nonslender wings
and the change of the lift coefficient. Hence, vortex breakdown is not a limiting
phenomenon as far as the lift force is concerned for nonslender wings. On the
contrary, flow reattachment is key to any flow control strategy as suggested in
Figure 1.
3.2 Passive Control with Wing Flexibility
Passive lift enhancement for flexible delta wings has been demonstrated as a potential
method for the control of vortex-dominated wing flows [30]. Force measurements
over a range of nonslender delta wings (with sweep angles = 40 to 55) havedemonstrated the ability of a flexible wing to enhance lift and delay stall compared
with a rigid wing of similar geometry. An example for = 40 is shown in Figure 4a.This recently discovered phenomenon appears to be a feature of nonslender wings.
Flow visualization, PIV and LDV measurements show that flow reattachment takes
place on the flexible wings in the post-stall region of the rigid wings. The lift increase
in the post-stall region is accompanied with large self-excited vibrations of the wings
as shown in Figure 4b. The dominant frequency of the vibrations of various
nonslender delta wings is St = O(1). These vibrations promote reattachment of theshear layer, which results in the lift enhancement. Various measurements including
wing-tip accelerations, rms rolling moment, and hot-wire measurements confirm that
the dominant mode of vibrations occur in the second antisymmetric structural mode in
the lift enhancement region. The self-excited vibrations are not observed for a half-
wing model, hence passive flow control for a flexible wing occurs only in the
anti-symmetric mode.
Fig. 4. (a) Variation of lift coefficient as a function of angle of attack for rigid and flexible
wings, = 40; (b) Variation of mean and amplitude of fluctuating wing-tip deflection with
incidence, =40
CL
0 5 10 15 20 25 30 35 400
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
1.1
1.2
1.3
1.4
1.5
Flexible
Rigid
/s
0 5 10 15 20 25 30 35 40 450
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
0.18
0.2
Mean deflection
Peak-to-peak amplitude
(a) (b)
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144 I. Gursul et al.
Spectral analysis of velocity fluctuations [31] along the shear layer showed large
sharp peaks, corresponding to the wing vibrations. There are also broad dominant
peaks in the spectra of velocity fluctuations in the range of St = 1 to 5 for the post-
stall incidences, and these correspond to the shear layer instabilities. The center
frequency of these peaks decreases with streamwise distance as the shear layervortices shed conically. There is also a decrease in the spanwise direction due to the
vortex pairing process. The frequency of the structural vibrations is in the same range
as these natural frequencies [31].
3.3 Active Control of Reattachment
Rigid delta wings undergoing small amplitude oscillations [32] in the post-stall region
exhibit many similarities to flexible wings, including reattachment in the post-stall
region (see Figure 5). For simple delta wings and cropped delta wings [31] with =
50, 40, and 30, an optimum frequency around St = 1 was identified for which thereattachment is observed. Note that these dramatic changes are observed with
unsteady forcing in the post-stall region, whereas there is little effect in the pre-stall
region. Hence active control methods in the form of leading-edge oscillations or
blowing can be effective.
An important parameter is the wing sweep angle. The effect of excitation on a
swept wing is similar to the response of the flow over a backward-facing step [33] to
the periodic excitation. However, for zero sweep angle, formation of a closed
separation bubble at high angles of attack in the post-stall region is not possible. It
seems that moderate sweep angles (around 50) help the formation of semi-openseparation bubbles, hence the wing sweep is beneficial in flow reattachment.
However, there is a lower limit of sweep angle below which the beneficial effect of
wing sweep will diminish. This lower limit of sweep angle is around = 20.Symmetric perturbations in the form of small amplitude pitching oscillations
(1 amplitude) were studied for = 50 simple delta wing. The results show thatsymmetric perturbations also promote reattachment and vortex re-formation. Hence,
Fig. 5. Effect of shear layer excitation for =25 and =50; (a) time-averaged fluorescent dyevisualization, (b) instantaneous visualization for one side only
(a)
(b)
St=0 St=1.0
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Control of Wing Vortices 145
for active control purposes, both symmetric and anti-symmetric excitations are
effective. However, passive control for a flexible wing occurs only in the anti-
symmetric mode.
3.4 Vortex Re-formation
Within the reattachment region, axial flow may develop, resulting in re-formation of
the leading-edge vortices. Figure 6 shows an example of vortex re-formation [32],
which occurs when the amplitude of forcing is sufficiently large and the frequency of
excitation is near an optimum value. The mean breakdown location becomes a
maximum at an optimum frequency as shown in Figure 7.
Fig. 6. Flow visualization for stationary and oscillating wings in water tunnel, = 50, =25
fc/U
xbd
/c
0 1 2 3 4 5 6 7 8 9 100
0.1
0.2
0.3 = 25, = 5 = 25, = 1
Fig. 7. Variation of time-averaged breakdown location as a function of dimensionless
frequency for two values of oscillation amplitude, = 50, =25
The time-averaged vorticity flux increases due to the oscillating leading edge,
which leads to increased circulation. Although the leading edge vortices becomestronger due to the leading edge motion, vortex breakdown is delayed for the
oscillating wing compared to the stationary wing for which breakdown is at the apex.
This appears to be in contrast to the well-known studies of vortex breakdown, which
indicate that increased strength of vortices should cause premature, rather than
fc/U = 0 fc/U = 1.8
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146 I. Gursul et al.
delayed, breakdown. This result suggests that streamwise pressure gradient might be
modified favourably due to the wing motion.
4 High Aspect Ratio Wings
4.1 Vortex Control Concepts
Control of formation and development of tip vortices in both near-wake and far-wake
has potential benefits in a variety of aerodynamic problems. Tip vortices form in a
similar way to the leading-edge vortices over low aspect ratio wings and the roll-up
process becomes complete within a few chord-lengths downstream of the trailing-
edge.
There appear to be three main applications of flow control approaches with regard
to the tip vortices: 1) reduction of induced drag, 2) attenuation of vortex wake hazardon following aircraft, 3) reduction of helicopter noise due to the blade-vortex
interaction. These will be briefly reviewed with regard to vortex control concepts.
For reduction of induced drag, various methods were considered [34], including
planform shape and span, tip shape, winglets, fences and tip sails. Wing tip devices
are used to redistribute the vorticity near the wing tip. Similarly, any flow control
method that can displace the tip vortices in the outboard direction can be used to
reduce the drag as it is inversely proportional to the square of the spanwise distance
between the vortices.
In order to attenuate wake vortex hazard on following aircraft, the core size of the
vortices can be increased by turbulence injection into the core. Various wing tip
devices were tested, which were found to be not much effective in the far-wake.
Those that seemed to decrease the vortex hazard (such as decelerating chutes and
splines placed behind the trailing-edge) had an unacceptable drag penalty [35]. It was
noted [36] that passive devices in the form of turbulence generators could increase the
size of the vortex core and also promote cooperative instabilities as an additional
benefit. A second and more promising method is to rely on the longwave
instabilities occurring in a system of several vortices [37]. Compared to the
alleviation of a single vortex by turbulent diffusion, excitation of the long-wave
cooperative instabilities of multiple vortices has the potential for much fasterdestruction of vortex wakes. Hence deliberate creation of multiple vortices and
excitation by oscillating surfaces or oscillatory blowing may be a promising strategy.
One of the sources of helicopter noise is the interaction of rotor blades with the
vortices shed from preceding blades. Noise and vibration caused by this interaction
can be reduced by i) increasing the distance between the rotor blade and tip vortex,
and (ii) by increasing the size of the vortex core and decreasing the maximum
tangential velocity.
4.2 Tip Blowing
Most of the intended modifications to the tip region (such as wing tip devices), to the
vortex location, strength, and structure can be achieved without the use of passive
devices. Active flow control using wing tip blowing can achieve multiple tasks
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Control of Wing Vortices 147
during different flight regimes. It was shown that the strength, location, core
structure, and number of vortices can be effectively manipulated by tip blowing [38].
The effect of continuous blowing using high-aspect ratio jets is very sensitive to
the blowing direction. The location and strength of the vortices generated by the jet
and their interaction with the tip vortex lead to different flow configurations.Blowing in the upward direction produces additional co-rotating vortices in the near-
wake as shown in Figure 8. These strong vortices forming on the wing surface can be
used to increase the lift in certain applications such as hovering rotorcraft. Figure 9
shows that a diffused vortex is obtained with spanwise blowing near the pressure
surface. Also, downward blowing produces diffused vortices. For these cases,
blowing appears to add a substantial amount of turbulence in the vortex core,
resulting in diffused trailing vortices. For downward blowing, it was possible to
displace the vortices in the outboard direction, which should result in an induced drag
Fig. 8. Vorticity distribution for upward blowing
Fig. 9. Vorticity distribution for spanwise blowing near the pressure surface
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148 I. Gursul et al.
(b)
fc/U
U/U
0
10-1
100
1010.6
0.8
1
1.2
synthetic jet - C=0.0004synthetic jet - C=0.0008continuous jet - C=0.0004
y/c
z/c
-0.1 0
0.1 0.2 0.3-0.1
0
0.1
0.2
0.3
Fig. 10. (a) Velocity and vorticity for the synthetic jet (with no freestream); (b) variation of
maximum tangential velocity at x/c=1.0 as a function of dimensionless frequency
reduction. Spanwise blowing also results in a lift augmentation [39] as the downwash
decreases with blowing. Drag reduction and lift augmentation are essentially inviscid
phenomena due to an effective increase in span and aspect ratio of the wing.
Synthetic jets can be useful for wing tip blowing as the air supply problem is
avoided. Figure 10 shows that a synthetic jet is beneficial in terms of diffusing the
trailing vortex [40]. Synthetic jets produce large turbulence and much larger vortex
wandering. For the blowing coefficients used, the effect of excitation frequency was
minor. While there are substantial changes in the circulation of the trailing vortex for
continuous jets, the circulation remains virtually the same for synthetic jets. The
intermittent and diffused jet vortices are weak and do not appear to affect the totalcirculation.
5 Conclusions
For slender delta wings, control of vortex breakdown has been the primary goal of
many investigations. Delay of vortex breakdown is possible with the modifications to
the swirl level and pressure gradient. The use of control surfaces such as leading-
edge flaps makes it possible to control the location, strength, and structure of the
vortices. Blowing and suction at the leading-edge, trailing-edge, or along the core
have differences in terms of their effects on swirl level and pressure gradient affecting
the vortex core. Along-the-core blowing is the most effective method for delaying
vortex breakdown. Active flow control using high-frequency excitation targets the
Kelvin-Helmholtz instability of the separated shear layers. In contrast, low-frequency
excitation appears to modify the external pressure gradient only.
For nonslender delta wings, flow reattachment is the most important aspect for
flow control methods. Passive lift enhancement on flexible wings is due to the self-
excited wing vibrations, which promote flow reattachment in the post-stall region.
The frequency of the wing vibrations (St = O(1)) is in the same range as the naturalfrequencies of the shear layer instabilities. Rigid delta wings undergoing small
amplitude oscillations in the post-stall region exhibit many similarities to flexible
wings, including reattachment and vortex re-formation. Moderate sweep angles help
the formation of semi-open separation bubbles, hence the wing sweep is beneficial.
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Control of Wing Vortices 149
For high aspect ratio wings, vortex control concepts are diverse, ranging from drag
reduction to attenuation of wake hazard and noise. Modifications to the vortex
location, strength, and structure are common ideas in these applications. Active flow
control using wing tip blowing is shown to have potential for various objectives.
Depending on the blowing configuration and direction, more diffused or strongervortices, and also, multiple vortices, that move inboard or outboard can be generated.
The deliberate creation of multiple vortices and excitation of vortex instabilities may
be a promising strategy for effective control in the far-wake.
Acknowledgements
The authors acknowledge the financial support of the Air Force Office of Scientific
Research (AFOSR), Engineering and Physical Sciences Research Council (EPSRC)
and the Ministry of Defence in the UK.
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