INTRODUCTION
In the nature, birds and insects fly by flapping their wings in the air to
obtain enough aerodynamic force to support and propel them. Disclosing the flight
mechanisms of these birds and insects can be very instructive for the development
of Micro Air Vehicle (MAV). Numerous investigations on the stroke motion of
flapping wings of birds or insects in a forward flight have been carried out,
such as the studies by WeisFogh, (1956), Zarnack
(1988), Dudley and Ellington (1990), Tobalske
and Dial (1996), Willmott and Ellington (1997),
Schilstra and Hateren (1999), Norberg
and Winter (2006) and Tian et al. (2006)
pertaining to aerodynamic forces, controlabilities and propulsive characteristics
of the flapping wings. These experimental studies are essential since they are
very helpful to explore how the wings delicately move to keep the stability
and the flexibility of flight. However, they are limited in revealing the aerodynamic
performance of a wing in forward flight since it is not feasible in these experiments
to find a representative wing kinematics of the free forward flight. Recently,
much effort has gone into the design and construction of devices propelled by
flapping such as the MAV with flapping wings, where one of the primary design
challenges in these efforts has been the understanding of the unsteady fluid
mechanics of flapping.
The generation of thrust by an oscillating airfoil has a notable effect on
the structure of the wake. The flow pattern behind a slowly oscillating airfoil
consists of a K'arm'an vortex street similar to that behind a bluff body and
the sense of rotation of the vortices is a result of the momentum deficit behind
the structure corresponding to net drag. Conversely, the wake is inverted and
the vortices have the opposite sense of rotation to that behind a bluff body
if the airfoil oscillates more energetically, which indicates a jet of fluid
behind the airfoil and the development of thrust. Lai and
Platzer (1999) performed an experiment of flow visualization on the flow
patterns generated by a plunging airfoil. They reported that the vortex patterns
generated by the plunging airfoil change from dragproducing wake flows to thrustproducing
jet flows as soon as the ratio of maximum plunging velocity to freestream speed
exceeds approximately 0.4. Schouveiler et al. (2005)
experimentally investigated the influences of Strouhal number and the maximum
angle of attack on the propulsive performance of a harmonically plunging airfoil.
Their results showed that the pattern of the vortices shed in the wake is associated
with the behavior of the angle of attack. They also used a biasangle mechanism
to break the symmetry of the foil motion with respect to the flow while the
up and down stroke duration times were kept the same. In a biology experimental
study, Ennos (1989) filmed some Diptera in free flight
using a highspeed cinematography and found that the flow circulations during
the two halfstrokes were unequal indeed. Also, Park
et al. (2004) found that the ratio between upstroke and downstroke
durations of many birds and insects are not the same. It is known that the difference
in duration time of up and down strokes plays important roles in the generation
of lift and thrust forces. However, the details of how this difference affects
the aerodynamic performance of flapping wings are still not fully understood.
Many numerical investigations on an oscillating airfoil have been also carried
out. Tuncer and Platzer (1996) investigated the mechanisms
of thrust generation for a single flapping airfoil by employing a multiblock
NavierStokes solver, where the unsteady flow field around the flapping airfoil
was analyzed. Their results showed that the propulsive efficiency of a single
airfoil can be more than 70% when a flapping amplitude of 0.4 chord length and
a reduced frequency of 0.1 are specified. Lewin and HajHariri
(2003) numerically examined the flow characteristics and power coefficients
of an elliptical airfoil heaving sinusoidally over a range of frequencies and
amplitudes. Their simulations produced a periodic and symmetric solution for
a given Strouhal number of 0.25. They found that the separation of the leading
edge vortices at low heaving frequencies leads to diminished thrust and efficiency
and, at high frequencies the efficiency decreases similarly to inviscid fluid.
Zhu et al. (2008) investigated the aerodynamic
performance of dual harmonic flapping airfoils and found that the dual flapping
airfoils in a tandem configuration can have better propulsive efficiency than
a single flapping airfoil. In above mentioned the numerical studies the duration
times for up and down strokes are the same, and none of these numerical studies
has discussed the flapping mechanism of a plunging wing consuming different
up and down stroke duration times or undergoing a nonsymmetrical plunging motion.
The present study aims to increase the fundamental understanding of aerodynamic
performance of a flapping airfoil in a uniform flow undergoing a nonsymmetrical
plunging motion. The symmetrical characteristics with respect to the incoming
flow is purposely broken and the focus of this study is on the effects of the
nonsymmetrical plunge with unequal time between downstroke duration and upstroke
duration, and the attack angle of the airfoil on thrust, lift and wake structure.
Airfoil NACA0014 is considered and the finite volume method is used to solve
the governing equation of fluid flow. Only twodimensional fluid flow is considered.
Though in practice the fluid flow around a flapping wing is three dimensional,
the present study still will be of fundamental use in exploring the aerodynamic
features of a flapping wing undergoing nonsymmetrical motions, and in getting
into the physical understanding of creature flying mechanisms.
PROBLEM DESCRIPTION
Physical model: An airfoil undergoing a plunging motion in a uniform flow with a constant attack angle with respect to the uniform flow is considered, which is to simulate a flapping wing in a forward flight. The effective attack angle changes all the time since the airfoil undergoes the plunging motion in a uniform flow. A schematic configuration of the problem is shown in Fig. 1 where a twodimensional NACA0014 airfoil with chord c of infinite span is employed. α is the attack angle with respect to the uniform flow and 2h_{0} c is twice the amplitude of motion measured from the mean position. U_{∞} is the velocity of the uniform flow.
Plunging motion kinematics: The flapping motion of the flying insects
includes alternative upstoke and downstroke periodic motions and experience
different time durations for up and down strokes. It is known that flying insects
change the time ratio between downstroke and upstroke duration in order to
get an alterant force for flight. The plunging motion model employed here with
different time ratios between downstroke and upstroke durations is concluded
from the kinematics analysis of some insects such as desert locust, hawkmoth
etc. in a forward flight (WeisFogh, 1956; Willmott
and Ellington, 1997; Ennos, 1989) and the kinematics
equation of the model is extracted from the experimental data of these insects
with the fewest number of parameters (see appendix).

Fig. 1: 
Schematic configuration of a rigid airfoil undergoing a plunging
motion in a uniform flow 
In this model the plunge displacement h(t) with the plunging period T = 2π/ω
can be expressed by the following Fourier equation (Willmott
and Ellington,1997)
where, a_{0,} a_{n,} b_{n}, c_{n} and d_{n} are coefficients of Fourier equation. This model can give a prescribed plunging motion with unequal duration for up stroke and down stroke, and importantly it ensures all the continuities of displacement, velocity and acceleration between different half cycles which can not be ensured by a simple sinusoidal plunging model when an unequal duration time is specified.
A number of cases are examined where for each case the nondimensional plunging amplitude h_{0} is kept at the same value of 0.4. The duration time ratio is defined by:
where, t_{d} is the duration time of down stroke and t_{u } up stroke. Seven different time ratios are selected according to the results of fitting between the available experimental data and the plunging model (1) and they are 0.60, 0.80, 0.82, 1.00, 1.22, 1.26 and 1.68. The detail of how to fit the experimental data with the plunging motion model is described in the appendix. The displacements of the plunging motion for seven different time ratios are illustrated in Fig. 2.
When τ = 1.00, the airfoil will follow a symmetrical down and upstroke pattern and the displacement Eq. 1 becomes a sinusoidal function identified as one special Fourier equation where all the coefficients are zero except a_{1}=h_{0}=0.4.
METHOD OF SOLUTION
Governing equations and solver: The governing equations for unsteady,
incompressible and viscous fluid flow can be written in the following form:
with the twodimensional Cartesian components, F_{Kj} is given by:

Fig. 2: 
Kinematics with different down and upstroke duration times 
where, U_{j }U_{k} is the Cartesian velocity components, Û_{j}
the mesh velocity, P the pressure and δ_{jK} the Kronecker Delta
number. The Reynolds stress tensor
is given by:
where, v_{t} is the eddy viscosity determined by the turbulence model
and k is the turbulent kinetic energy. The above timedependent Navierstokes
equation are solved using the finite volume method (Rhie
and Chow, 1983; Versteeg and Malalasekera, 1995) and
the Shear Stress Transport (SST) kω turbulence model is used in the present
work. SST as a low Reynolds number model models the Reynolds stress with two
transport equations for the turbulent kinetic energy and the specific dissipation
rate ω, respectively. The wall functions are not used. One can refer to
Menter (1993) for a detailed description of the SST model.
The Pressure Implicit with Splitting of Operators (PISO) algorithm (Issa,
1985; Issa et al., 1991) is employed to deal
with the coupling between the pressure and velocity. The thirdorder accurate
QUICK scheme (Leonard, 1979) is used to discrete the
convective terms. These numerical algorithms are quite standard now.
The total computational domain is 18c long and 10c wide. A conformalhybrid
grids system that consists of quadrangular meshes in an internal domain around
the airfoil and triangular meshes in an outer field is used as shown in Fig.
3. The complete inner mesh moves according to the wing kinematics and a
dynamic deformable remesh method in accordance with Geometric conservation law
method (Lesoinne and Farhat, 1996 ) is used in the outer
field.

Fig. 3: 
Computational grid around the plunging airfoil 
A series of tests for grid independent and time step independent were conducted
before actual calculations were carried out. Based on these tests, element number
about 4.2x10^{4} and time step 0.0025T are selected for all the cases.
The incoming flow runs from the left to the right. At the inlet of the computational domain, a uniform profile is prescribed:
The right outlet is far away enough so that a boundary condition of fully developed flow is given, i.e.,
The noslip boundary condition is specified at the airfoil surface and a symmetry
boundary condition (Elhadi et al., 2002) is applied
at the lateral faces of the computational domain. The influence of this symmetry
condition has been investigated and found to be sufficiently adaptive. The simulation
starts assuming the fluids is initially at rest.
Important parameters: The Reynolds number, which characterizes the effects of viscous, is defined as:
where, ρ is the density of fluid and μ the dynamic viscosity.
The Strouhal number, which characterizes the periodicity in a flow field, is defined as:
where, f is the frequency of plunging motion.
The reduced frequency is defined as:
For all calculations, the Reynolds number is set at 10^{4} and the reduced frequency is kept at 2 which results in a Strouhal number of 0.255.
The lift and drag coefficients are computed from:
where, s is the surface area per unit spanwise length of the airfoil and F_{y }and F_{x} are instantaneous lift and drag forces, respectively. These forces are calculated from the integration of the pressure and the viscous force on the surface of the airfoil.
The periodaveraged thrust and lift can be evaluated as:
where, F_{x}(t) and F_{y}(t) represent the instantaneous force components in x and y directions respectively. Then, the mean vertical force coefficient C_{V} is defined as:
The mean thrust coefficient C_{Thm }is defined as:
RESULTS AND DISCUSSION
Validation: A series of validation tests for the computation code are
conducted before actual calculations are carried out and the results are compared
with related experimental and numerical results published in the literature.
One of the comparisons is shown in Fig. 4 where the time history
of the drag coefficient for the airfoil plunging in the uniform flow with τ
=1.00, α = 0, k = 2, St = 0.255 and Re = 10^{4} is plotted against
the dimensionless time t’ = tU_{∞}/c. It is seen that the
result agrees well with the results of Tuncer and Kaya (2003)
and Miao and Ho (2006) for the same problem when the
flow settles down to a steady state at around t’ = 6 from an impulsive
start.

Fig. 4: 
Comparison of the drag coefficient time histories 
The vorticity contours around the airfoil for the times of t/T = 0.25, 0.5,
0.75 and 1.00 are illustrated in Fig. 5ad,
respectively. During the down stroke (Fig. 5a, b),
the clockwise vortex filaments roll up into a large leading edge vortex on the
upper side of the airfoil and the counterclockwise vortices produced by last
half cycle truncate the vortex band at the tailing edge (Fig.
5c, d). Then the truncated vortex advects to downstream
(Fig. 5d). During the up stroke, similar process repeats and
the counterclockwise vortices gradually grow up and roll up into a large vortex
on the lower side of the airfoil. The alternatively shed vortices form a vortex
street in the downtream of the airfoil similar to that behind a bluff body.
However, the difference is that the counterclockwise vortices here are in the
upper line of the street while the clockwise vortices in the lower line, which
indicates that the wake is inverted and the vortices have the opposite sense
of rotation to that behind a bluff body. Consequently, thrust rather than drag
is generated. The present reverse Von Karman vortex street formed behind the
plunging airfoil is in agreement with the experimental observation of Von
Karman and Burgers (1935).
Overall comparison on forces for the plunging cases: To investigate the effects of nonsymmetrical characteristics on the aerodynamic performance of the airfoil, seven attack angles ranged from 5° to 10° with an increase of 2.5° are examined for each time ratio. The variations of the period averaged values of thrust coefficient, vertical force coefficient with the attack angle are studied. Normally a period averaged value is calculated over ten cycles of the plunging motion after a steady status is reached.
Figure 6 shows the variation of C_{Thm} with angle
α for seven different values of τ where α is ranged from 5°
to 10° with intervals of 2.5°. It is seen immediately from the figure
that when the attack angle α is zero, an asymmetrical plunging motion of
the airfoil produces larger average thrust than the symmetrical one (i.e., the
balck unmarked curve in Fig. 6) and the average thrust reaches
a maximum value at both τ = 1.62 and 0.60. For each fixed α, there
is at least one nonsymmetrical plunge can provide a higher thrust than the symmetrical
plunge. Moreover, the way of the average thrust C_{Thm} varying with
α is different for different values of τ, which indicates that whether
one asymmetrical stroke motion produces higher thrust than the symmetrical case
is also affected by the attack angle α. An appropriate combination of τ
and α will generate a better thrust, for example, when the airfoil plunges
in an asymmetrical stroke motion with τ = 0.60 and α = 5°, it
will generate the highest thrust for the cases considered. The attack angle
α with respect to the incoming flow can modify the thrust to make the flight
speed up, slow down or uniform. This is consistent with the observation on hawkmoths
by Willmott and Ellington (1997) where they found that
the increases in forward flight speed of the hawkmoths always tended to be accompanied
by an increase in their stoke plane angle and a decrease in their body angle
which results in a change in the attack angle with respect to the incoming flow.
The mean vertical force coefficient is plotted as a function of α in Fig. 7. It can be seen that the vertical force produced by the symmetrical motion increases with α almost linearly, while for the nonsymmetrical cases, the force dose not always increase monotonically. As an example, for the nonsymmetrical case of τ = 0.80, the force increases first and reaches a maximum value at α = 2.5°, and then decreases. Figure 7 also shows that the nonsymmetrical character with different ratios between the down and up stroke duration has a significant effect on the generation of vertical force when the forward flight airfoil plunges with a fixed inclination. For the practical forward flight, the positive mean vertical forces can be used to offset the payload or provide an ascending flight, while negative mean vertical forces will cause the flight moving downward. Form the above results, it can be seen that the aerodynamic forces can have many varieties of change by adjusting the nonsymmetrical character of wing motion no matter the attack angle changes or not. These results indirectly explain why most stoke motions of the flying insects are nonsymmetrical patterns.
Figure 8 shows the ratio of mean vertical force coefficient
to mean thrust coefficient versus the time ratio τ. The ratio η =
C_{v}/C_{Thm} can be one of criteria to assess the performance
of the flapping flight. In order to facilitate comparison the symmetrical plunge
motion with τ = 1.00 is chosen as the baseline in the discussion. It can
be seen that there is at least one nonsymmetrical plunge that can carry more
loads during the uniform flight at a fixed attack angle.

Fig. 5: 
(ad) Vorticity contours for a symmetry plunge motion with
α = 0; (blue: clockwise; red: counterclockwise) 

Fig. 6: 
The periodaveraged thrust coefficients with respect to angle
α computed at k = 2 

Fig. 7: 
Variations of averaged vertical force coefficients withα
for different values of τ 
For an example, when α is kept at 10°, the nonsymmetrical plunge
with τ = 0.80, 0.82, 1.22 and 1.68 provide bigger values in mean vertical
force coefficient to mean thrust coefficient ratio than the case τ = 1.00.

Fig. 8: 
Variations of ηwith respect to time ratio τ.
between down to upstroke 
However, not all the nonsymmetrical plunges provide good performance assessed
by the mean vertical force coefficient to mean thrust coefficient ratio (e.g.
τ = 0.60).
Wake structures of nonsymmetrical plunge between down and up stroke:
To further analyze the effect of nonsymmetrical plunging motion on the aerodynamic
performance of an airfoil, the vorticity structures in the wake of the airfoil
undergoing a plunging motion with a constant attack angle with respect to the
incoming flow but different time ratio of down and upstroke duration are illustrated
in Fig. 9af. Though the vortex shedding
patterns are definitely different for different values of τ, it can be
seen that the reverse Von Kαrmán street pattern persists in every
present result, although largely weakened in some case. Both symmetrical and
nonsymmetrical stroke patterns produce a positive mean thrust as indicates by
Fig. 6.

Fig. 9: 
(af) Vorticity contours for nonsymmetry plunge with different
downup time ratio when α = 0° and kh_{0} = 0.8. (blue:
clockwise) 

Fig. 10: 
(af) Vorticity contour for nonsymmetry plunge with τ
= 1.26 when the airfoil at highest position. (blue: clockwise) 
Current results also show the wake pattern of the airfoil is determined by the formation and the growth of both the LEV and the TEV and also the interaction between them. The timing of the separation of the Leadingedge Vortex (LEV) and Trailingedge Vortex (TEV) is closely similar for one nonsymmetrical motion.

Fig. 11: 
(af) Vorticity contour for nonsymmetry plunge with τ
= 1.68 when the airfoil is at highest position. (blue: clockwise) 
Once the motion is determined, the corresponding pattern of vortex street resulted
from the fate of LEV and TEV could be existent. As an example, for the case
with τ = 1.26 (Fig. 10af) the shedding
mechanisms of the vorticity is the same expect the transfer direction of the
vortex street. There is a little difference in the second shed off vortex in
upper branch of the vortex street (Fig. 10 α = 5°,
7.5°), which is evidence for the intensity of the LEV weakly affected by
the α.
Besides the vortex pattern in the wake, the trend of vortex street is also
decided by the plunge pattern. When α = 0°, the trend of street produced
by the symmetrical plunge motion is level. Nevertheless, the vortex street of
the nonsymmetrical patterns deflected a little from the level which result that
the mean vertical force coefficients is nonzero as shown in Fig.
6a. A similar deflection of the street was experimentally observed by Lai
and Platzer (1999) at a larger St (St>0.6) using a sinusoidally symmetrical
plunge.
For each nonsymmetrical plunging motion, the angle of attack also has a significant affect on the trend of the vortex street. Figure 10 shows the vortex street with τ = 1.26 for different values of α ranging from 5° to 10° in an interval of 2.5°. The vortex structure in the wake are closer the same except the inclination of the vortex street. When the vortex street is downwardsloping the higher mean vertical force could be produced such as the case with α = 5° provide 44% lift higher than the α = 5° case. When the trend of the street near to the level, the bigger mean thrust appears such as the case with α = 5 ° provide 18.4% thrust higher than that one when α = 5°. Additional, it can be found that the intensity of the second shed vortex in the near rear region has a slight change as the angle α increases.
Additionally, it should be noted that there are different formations of shedding
vortices per cycle in the vortex street when α = 0° as shown in Fig.
9. For a symmetrical plunging motion, there are two vortices shed from the
airfoil per cycle whereas for a nonsymmetrical plunging motion with a fixed
reduced frequency and amplitude, there may be two or four vortices shed per
cycle. Figure 11af show that there are
four vortices shed in to the wake per cycle when τ = 1.68. It can be considered
that there are two tiers of the streets after the rear of the wing. The distribution
of two tiers located upper and lower respect to the centerline of wake. The
LEV pairs up with the TEV but the two do not immediately merge which result
in a much wider wake than those in the other cases. Lewin
and HajHariri (2003) found a similar but not the same format in the vortex
street at kh_{0} = 1.0 and a higher reduced frequency with the symmetrical
plunge motion. Their results show that the location of two tiers is symmetrical
about the mean position of the wake when α is zero. While our shedding
format is also fourvortices, the distribution of the tow tiers is not symmetrical
respect to the mean position of wake and the difference in vortex intensity
between the two tiers exists either. This asymmetric distribution makes the
mean thrust get higher values at small attack angles (Fig. 6).
When the stronger tier locates in the upper side of wake, a higher mean vertical
lift appears. Such as the nonsymmetrical pattern with τ = 1.68 provides
higher mean values both lift and thrust. Whereas, the weaker tier locates in
the upper, the mean vertical lift attain a lower value (e.g., τ = 0.6).
The above results reveal that fate of the LEV and TEV is mainly determined by the motional pattern and the strength of the LEV and TEV is weakly affected by the attack angle. The propulsive force decided by the formation of the wake structure which results from the development of the LEV and the TEV. Whether the plunging pattern is symmetrical or not has the predominant effect on the formation of vortex street in the wake. Summarizing, the nonsymmetry moving patterns used by the flying bio is one of significantly factor to improve the performance of forward flight. These lead to the suggestion that the flapping vehicles may adopt sets of nonsymmetrical plunging motion with different time ratios between downstroke and upstroke during to improve the thrust performance and level the loads over the forward flight.
CONCLUSIONS
A comprehensive numerical simulation for a NACA0014 airfoil stroking up and down in a uniform flow has been carried out using the finite volume method. The flow is assumed to be twodimensional, the Reynolds number is kept at 10^{4} and the reduced flapping frequency is set at 2. In particular, the nonsymmetrical characteristics caused by the time ratio between the down and up stroke duration have been studied. The lift, thrust, lifttothrust ratio have been computed to assess the nonsymmetrical effects on the forward flight. The corresponding wake structures of the airfoil have been analyzed. It has been shown that the nonsymmetrical motion indeed can enlarge lift, thrust or even both of them during the forward flight. Further, current numerical results confirm that the nonsymmetrical motion of insect wings plays an indispensable role during their flight and can make their flight much more effective and flexible.
Present results show that all the periodaveraged thrusts are positive for the cases studied and a reversed Von Karman vortex street always exists for both symmetrical and nonsymmetrical plunging motions. For the cases with unequal duration time between down and upstroke, there always exists at least one nonsymmetrical plunging motion which produces much bigger mean thrust or vertical mean force than the symmetrical motion. This has a close relationship with the formation of the vortex street. The nonsymmetrical plunging motions adjust the development of the LEV and TEV, and also the interaction between them, which results in the changes in the formation of the vortex street in the wake of the plunging airfoil. The trend of this reverse Von Karman street is found to be also affected by the attack angle for both symmetrical and nonsymmetrical plunge.
Two types of vortex pattern in the wake have been observed. One has two vortices shed in each plunging cycle and the other has four. For the wake with twovortices shed per cycle, higher mean vertical lifts will be produced when the vortex street advects downwards. When the trend of the wake is near to the level, a higher periodaveraged thrust appears. Also, both the symmetrical and nonsymmetrical plunging motion can produce the fourvortices shed pattern in the wake, but the detailed distribution is different. When the attack angle is zero, two tiers of vortices locate after the airfoil symmetrically above and below the mean position. However, the situation for the nonsymmetrical plunging motion is quite different. Apart from the nonsymmetrical location of the two tiers, the vortex intensity between the two tiers is also different. The difference in the intensity of the vorticity between two tiers implies that the half stroke which spends longer time produces a weaker LEV and TEV.
Current study focuses on heaving pattern not considering the pitching model. For the simulative conditions mentioned above, the moving pattern is prerequisite to the characteristics of flow field around the plunging wings. For one of prescribed patterns, the Strouhal number, heaving amplitudes and oblique angles have the significant influence on the vortex shedding mechanism of plunging wing. The nonsymmetrical plunging motion is one of significant factors to improve the performance of the vehicles. This leads to the suggestion that the flapping vehicles may use the nonsymmetrical character of motion to alter the thrust and level the loading by adjusting the time ratio between up and down stroke duration over the forward flight. Present work emphasizes the unsteady effects and the results can be of help for the development of flapping vehicles assembled the bionical actuator and its controller. Future studies perhaps will dconsider the effect of deformation caused by load distribution along the wing surface and computation on the threedimensional rigid model need to be further performed.
ACKNOWLEDGEMENTS
The study described in this research was conducted in Shenzhen Graduate School, Harbin Institute of Technology and fully supported by a grant from National Natural Science Foundation of China (Project number No. 90715031). The financial support is gratefully acknowledged.
APPENDIX
For completeness we briefly describe the main method of dealing with the stroke
kinematics spending different time between up and down halfstroke. Take one
case when the time ratio τ = 1.26 as an example. Willmott
and Ellington (1997) filmed the course of wingbeats of a Hawkmoth spending
different time between downstroke and upstroke using highspeed video system
in an openjet wing tunnel. The experimental displacement is fitted in a form
of Fourier series as Eq. 1 as shown in Fig.
12a. The first and second derivative of Fourier equations is reasonable
continuous, which ensure that the adjustments on the velocity and acceleration
are always continuous. In order to transform the amplitude of the curve, the
conversion factor has been used. Then, through the translation to ensure that
the downstroke begin at the upper branch of the amplitude. Resultant figure
is depicted in Fig. 12b. Another, in order to further investigate,
a nonsymmetrical plunge with τ = 0.80 was constructed by mean of turning
the displacement of case with τ = 1.26. The plunging model with τ
= 1.26 spend the same time during downstroke with the case with τ = 0.80
in the upstroke cycle.

Fig. 12: 
(a) The fitted curve of a Fourier series when the time ratio
of downstroke to upstroke during is 1.26 and (b) the dimensionless displacement
of the model at τ = 1.26 
The treatment of the other unsymmetrical patterns such as τ = 1.22, 0.82
and τ = 1.68, 0.60 is in the same methods and the dimensionless displacements
of the plunging are shown in Fig. 2.