Abstract:
A vehicle includes a surface over which airflow passes. A plasma actuator is configured to generate plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of airflow from a surface of the vehicle includes generating plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Description:
CROSS REFERENCE TO RELATED APPLICATION 
       [0001]    This application is a non-provisional application claiming priority from U.S. Provisional Application Ser. No. 60/856,871, filed Nov. 2, 2006, entitled “Truck Tractor and Trailer Aerodynamic Drag Reduction Using Single Dielectric Barrier Discharge (SDBD) Plasma Actuators” and incorporated herein by reference in its entirety. 
     
    
     FIELD OF THE DISCLOSURE 
       [0002]    The present disclosure relates generally to drag reduction, and more particularly, to methods and apparatus for reducing drag via a plasma actuator. 
       BACKGROUND OF RELATED ART 
       [0003]    Trucks, such as for example, class-8 heavy duty trucks typically use significant amounts of fuel to move cargo across the nation. In most instances, very little attention has been paid to the major drag-producing design with the exception of a passive fairing placed over the tractor top and/or side to help close the gap between tractor and trailer. Separated flow typically exists over many of the surfaces to include the tractor-trailer gap, the rear end of the trailer and all along the under-carriage of the rig. It is known that overcoming the effects of drag oftentimes can require as much as two-thirds of the engine&#39;s power at a cruise speed of 70 miles per hour. Accordingly, class-8 truck gas mileage has not changed much in 15 years, and it is typically still between 5.5 and 6.5 miles per gallon. While some improvement has been made in efficiency, most of the gains have been negated by increases in cruise speed and higher gross weight limits. The use of an active flow control by plasma actuators can reduce the areas of separated flow which can make significant gains in rig efficiency, lowering the power and fuel consumption and improving the environmental emissions. 
         [0004]    Previous efforts to reduce the drag of these rigs have made some improvements, but so far have been slow to gain acceptance into the fleets because they interfere with the utility of the vehicle, require extensive power, are expensive modifications, show small improvements in fuel consumption and/or are not structurally sound enough to handle the day-to-day rough conditions that these vehicles experience. Some improvements have included fairings below the trailer body between the wheels, extension of the aft end of the trailer, and high speed injection of air into the flow. 
         [0005]    Plasma actuators have no moving parts, require very little power, can be incorporated into fairings and basic tractor and trailer structure, and show promise to greatly reduce the power and fuel consumption. They can be painted over and not even be seen by the casual observer. 
         [0006]    Plasma flow actuators provide a “body force” to the flow as the air passes over the surface. This “body force” accelerates the air, stabilizing the boundary layer and causing the air to remain attached to the surface even around tight radii to reduce or eliminate separated flow, a source of drag. By placing these actuators on the surface just before where the flow would ordinarily separate, the flow will remain attached which reduces drag. 
         [0007]    In one example, plasma actuators may be placed on fairings over the aft doors of the trailer to coax the flow around the corners, greatly reducing the turbulence and vortices behind these rigs. In another example, fairings may be incorporated into the doors for new trailers, and in yet another example, the same concept may be applied to the aft part of the tractor to cause the flow to stay attached behind the tractor. In still other examples, the forward part of the trailer may have actuators on its leading corners to keep the flow attached along the sides and top. In each of these examples, the gap-drag may thus be minimized leading to additional fuel savings. 
         [0008]    In another example, plasma actuators may be applied to the under-carriage of a vehicle to contain the flow and maintain attachment to assist in drag reduction. Still further, in each of the disclosed examples, the actuators may be turned off whenever the driver applies the brakes, to allow the drag to increase, thereby slowing the vehicle and reducing the braking needed. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0009]      FIG. 1  is a cross-sectional schematic illustration of an example single dielectric barrier discharge plasma actuator for use in reducing drag. 
           [0010]      FIGS. 2   a  and  2   b  are schematic illustrations of the example single dielectric barrier discharge plasma actuator of  FIG. 1  during half-cycles of an applied voltage waveform. 
           [0011]      FIG. 2   c  is a schematic illustration of a photomultiplier tube arrangement used to measure light emissions from an example plasma actuator. 
           [0012]      FIG. 2   d  is an illustration of an example light emission from an example plasma actuator as a function of the applied voltage. 
           [0013]      FIG. 2   e  is an illustration of an example light emission from an example plasma actuator as a function of the applied current. 
           [0014]      FIG. 2   f  is an illustration of an example light emission from the plasma actuator of  FIG. 2   e.    
           [0015]      FIG. 2   g  is a photograph of the plasma generated by an example plasma actuator. 
           [0016]      FIG. 2   h  is an illustration of the time to first light of the plasma as a function of the lateral (chordwise) distance of an example plasma actuator. 
           [0017]      FIG. 2   i  is a surface plot of the light emission of an example plasma actuator. 
           [0018]      FIG. 3  is circuit model of the example plasma actuator of  FIG. 1 . 
           [0019]      FIGS. 4   a  and  4   b  are schematic depictions of frequency and amplitude optimization, respectively, of an example plasma actuator. 
           [0020]      FIG. 5   a  is an illustration of positive and negative sawtooth voltage waveforms applied to an example plasma actuator. 
           [0021]      FIG. 5   b  is an illustration of positive and negative sawtooth current waveforms, corresponding to the positive and negative sawtooth voltage waveforms of  FIG. 5   a , applied to an example plasma actuator. 
           [0022]      FIG. 5   c  is an illustration of the light emission from an example plasma actuator for the example of the applied positive sawtooth voltage waveform of  FIG. 5A . 
           [0023]      FIG. 5   d  is an illustration of the light emission from an example plasma actuator for the example of the applied negative sawtooth voltage waveform of  FIG. 5A . 
           [0024]      FIG. 5   e  is an illustration of the thrust versus dissipated power of an example plasma actuator for both the applied positive and negative sawtooth voltage waveforms. 
           [0025]      FIG. 5   f  is an illustration of power dissipated in the plasma generated by an example plasma actuator. 
           [0026]      FIGS. 5   g  and  5   h  illustrate the induced velocity of air versus applied voltage for a square waveform and a triangle waveform, respectively when applied to an example plasma actuator. 
           [0027]      FIG. 5   i  illustrates the linear additive effect of an example plasma actuator. 
           [0028]      FIG. 5   j  is a smoke visualization of a cylinder showing the typical airflow around the cylinder. 
           [0029]      FIG. 5   k  is a smoke visualization of the cylinder of  FIG. 5   j , showing the energization of two example plasma actuators located on the diameter of the cylinder. 
           [0030]      FIG. 6   a  illustrates an example class-8 truck for use with the example plasma actuator of  FIG. 1 . 
           [0031]      FIG. 6   b  illustrates where on the example tractor and trailer the example plasma actuator of  FIG. 1  may effect drag. 
           [0032]      FIG. 7   a  illustrates an example of airflow behind a tractor or trailer while cruising at typical highway speeds. 
           [0033]      FIG. 7   b  illustrates an example configuration of plasma actuators mounted on a fairing attached to the back of the tractor or trailer. 
           [0034]      FIG. 8   a  is a smoke visualization of airflow around a four-inch radius surface in a wind tunnel without plasma actuators operating. 
           [0035]      FIG. 8   b  is a smoke visualization of airflow around the four-inch radius surface of  FIG. 8   a  with an example plasma actuator operating at a voltage of 28.5 kilovolts. 
           [0036]      FIG. 9  illustrates results showing the separation angle of the airflow as a function of radius, velocity of the airflow, and voltage of the plasma actuator, in an example wind tunnel test. 
       
    
    
     DETAILED DESCRIPTION 
       [0037]    The following description of various examples is not intended to limit the scope of the invention to the precise form or forms detailed herein. Instead, the following description is intended to be illustrative of the principles of the disclosure so that others may follow its teachings. 
         [0038]    Referring to  FIG. 1 , an example single-dielectric barrier discharge (SDBD) plasma actuator  1  is attached to a surface  3 , such as a fairing and/or a vehicle as will be described below. The actuator  1  may be attached to the surface such as, in particular, any region in which airflow separates from the surface  3 . The example plasma actuator  1  includes an exposed electrode  5 , a covered, insulated electrode  7  and a dielectric barrier material  9 . The exposed electrode  5  may be at least partially covered, while the insulated electrode  7  may be at least partially exposed. In this example, an alternating current (AC) voltage source  11  is electrically coupled to the electrodes  5  and  7 . 
         [0039]    Although the actuator  1  is shown in  FIG. 1  as extending from the surface  3 , it will be appreciated that the actuator  1  may be provided in a recess in the surface  3  so as to be partially or completely flush with the surface  3 . The electrodes  5  and  7  may be formed of any suitable conductive material, such as for example, copper foil. Similarly, the dielectric  9  may be formed of a suitable electrically insulating material, such as for example, a polyimide tape, such as KAPTON®. In the example plasma actuator  1 , the desired thickness of the dielectric  9  may be designed to be dependent on the maximum voltage that will be applied to the plasma actuator  1 . Polyimide tape is thin and flexible, but may degrade over time due to ozone generation in plasma. The dielectric  9  may also be a ceramic, such as MACOR®, which is typically machineable and durable. A dielectric formed of ceramic would typically need to be thicker than a dielectric formed of polyimide tape and be machined to its final shape. The dielectric  9  may also be a thermoplastic, such as for example, a semi-crystalline thermoplastic such as PEEK® film, which is thin and flexible and not affected by ozone. A thermoplastic film may also resist erosion caused by water. 
         [0040]    In operation, the application of high voltage by the voltage source  11  tends to cause air to ionize and create plasma. When the AC voltage is applied, a plasma discharge appears on the surface of the dielectric  9  above the covered electrode  7  and a directed momentum is coupled into the surrounding air. The momentum coupling alters the airflow over the actuator  1 . The plasma in the presence of an electric field E gradient, results in a body force vector f B  that acts on the airflow, as shown in  FIG. 1 . The body force is a body force per volume of plasma that varies in time and space during the AC voltage cycle. The body force vector f B  is defined by: f B =ρ C  E where ρ c  is the charge density of the plasma and E is the electric field gradient. Using the Boltzmann relationship, and substituting for ρ c , the body force vector can be rewritten as f B =(∈ o /λ D   2 )φE, where ∈ o  is the permittivity of the free space, λ D  is the Debye length (i.e. the characteristic length for electrostatic shielding in plasma), and φ is the electric potential. From this equation, it is clear that the body force from the plasma actuator  1  decreases with decreasing plasma density, i.e. increasing Debye length. 
         [0041]    Referring still to  FIG. 1 , in the example actuator  1 , the edges of the exposed electrode  5  and the covered electrode  7  are overlapped by a small amount in order to produce a more uniform plasma in the full spanwise direction of the surface  3 . If no overlap is provided, the air gap between the electrodes  5  and  7  tends to break down at the applied voltage before the dielectric  9 . At atmospheric pressure, almost any available dielectric material has a dielectric strength and breakdown voltage superior to air, and therefore air gaps typically are avoided in the design of the plasma actuator. If an air gap is present, the result is oftentimes a spanwise non-uniformity in the plasma, which tends to reduce the effectiveness of the plasma actuator. 
         [0042]    The example plasma actuator  1  of  FIG. 1  is a single dielectric barrier discharge (SDBD) plasma actuator. The example SDBD plasma actuator is stable at atmospheric pressure because it is self limiting due to charge accumulation on the surface of the dielectric  9 . In other words, the behavior of the plasma actuator  1  is primarily determined by the buildup of charge on the covered, insulated electrode  7 . When the AC voltage source  11  applies an AC voltage, a plasma discharge appears on the surface of the dielectric  9  above the covered, insulated electrode  7  and directed momentum, defined by the body force vector f B , is coupled to the surrounding air. The body force vector f B  may be tailored for a given application through the orientation and design of the geometry of the electrodes  5  and  7 . For example, the electrodes  5  and  7  may be designed to produce upstream or downstream oriented wall jets or streamwise vortices. 
         [0043]    Although the generated plasma is composed of charged particles, it is net neutral because it is created by the ionization of neutral air and an equal number of negative electrons and positive ions exist in the plasma. The charged particles respond to the external electric field and the electrons move to the positive electrode and the positive ions move to the negative electrode. This movement results in an imbalance of charges on the edges of the plasma that sets up an electric field in the plasma that is opposite to the externally applied electric field. The imbalance of charges on the edges of the plasma is due to the thermal motion of the charged particles in the plasma. The rearrangement of the charged particles continues until the net electric field in the plasma is neutralized. 
         [0044]    Referring to  FIGS. 2   a  and  2   b , a plasma is formed as a result of a series of discharges as electrons are transferred onto and off the surface of the dielectric  9 . As shown in  FIG. 2   a , when the applied voltage is negative, electrons move from the exposed electrode  5  to the dielectric  9 . As shown in  FIG. 2   b , when the applied voltage is positive, electrons move from the dielectric  9  to the exposed electrode  5 . The buildup of charge on the surface of the dielectric  9  is the reason that the discharge is self limiting and does not collapse into a constricted arc. Based on the energies, the electrons penetrate at most a few monolayers of the dielectric  9 . Due to the low conductivity of the dielectric  9 , the electrons generally remain at the location where they are deposited. The portion of the dielectric  9  that collects and includes the immobile electrons acts as a virtual electrode  13 , as shown in  FIG. 1 , in addition to the two electrodes  5  and  7  of the plasma actuator  1 . 
         [0045]      FIG. 2   a  represents the half cycle of the discharge for which the exposed electrode  5  is more negative than the surface of the dielectric  9  and the covered, insulated electrode  7 . The exposed electrode  5  thus acts as a cathode in the discharge. If the applied voltage is high enough, the exposed electrode  5  can emit electrons. Because the discharge terminates on the surface of the dielectric  9 , the buildup of the charge on the surface of the dielectric  9  opposes the voltage applied by the source  11 , and the discharge shuts itself off unless the magnitude of the applied voltage is continually increased. The behavior of the discharge is similar on the opposite half cycle shown in  FIG. 2   b  and a positive slope in the applied voltage is necessary to maintain the discharge. In the opposite half cycle shown in  FIG. 2   b , the surface of the dielectric  9  acts as a cathode. During the half cycle shown in  FIG. 2   b , the charge available to the discharge is limited to the charge deposited during the half cycle shown in  FIG. 2   a.    
         [0046]    Referring to  FIG. 2   c , a photomultiplier tube (PMT)  30  may be used to observe the bulk plasma with high time resolution. The light emissions observed by the PMT  30  are proportional to the dissipated current in the generated plasma. For the results shown in  FIGS. 2   d  and  2   e , the PMT  30  was arranged to observe approximately one third of the length of the plasma actuator  1 .  FIG. 2   d  shows two cycles of a plasma discharge that turns on and off during each cycle of the applied voltage. At a point “a” in the figure, due to some impedance mismatch in the driving circuit that applies the AC voltage, there is a momentary reversal in the slope of the applied waveform. Because the applied voltage is no longer becoming more negative, the discharge shuts off. At a point “b” in the figure, the applied voltage again resumes a negative course and the discharge reignites and stays ignited until the slope of the voltage waveform goes to zero, at approximately t=0.4 ms in this example. 
         [0047]      FIG. 2   e  shows one discharge cycle of the plasma actuator  1  with a sinusoidal applied voltage waveform. As shown in the figure, the discharge is more irregular on the positive-going half cycle than the negative-going half cycle.  FIG. 2   f  shows same data as  FIG. 2   e  but on a finer timescale. As shown in  FIG. 2   f , each pulse of light observed by the PMT  30  corresponds to a pulse in the current signal. However, not every current pulse corresponds to a light pulse. This is due to the fact that the PMT  30  only observes approximately one third of the plasma actuator  1 , while the current monitor measures the current during the entire discharge, thus there are discharges that do not occur in the PMT  30 &#39;s field of view. When the voltage on the exposed electrode  5  is negative-going, the discharge is relatively uniform across the width of the plasma actuator  1 . When the voltage is positive-going, the discharge is irregular, or “patchy.” The asymmetry in the discharge affects the efficiency of the momentum coupling to the flow, as described below. 
         [0048]      FIG. 2   g  shows an “open shutter” view of the plasma P (i.e. the shutter speed is longer than the period of the applied voltage waveform) generated by the example plasma actuator  1 .  FIG. 2   g  appears to show a plasma density gradient because the plasma nearest the edge of the exposed electrode  5  is brightest. However  FIG. 2   h  shows the relative time to first light as a function of lateral position of an aperture interposed between the plasma and the PMT  30 . As shown in the  FIG. 2   h , the plasma grows in the lateral (i.e. chordwise) direction at a constant rate. The plasma near the edge of the exposed electrode  5  thus appears brighter in  FIG. 2   g  due to its having emitted for a greater fraction of the discharge cycle, not because of a higher plasma density. It is also shown in the  FIG. 2   h  that the higher the applied voltage, the faster the plasma discharge spreads along the surface of the dielectric  7 . The propagation speed of the plasma discharge is also essentially the same for both the negative-going and positive-going half cycles for a given voltage. For both half-cycles, the discharge ignites at the edge of the exposed dielectric  7  and propagates along the surface of the dielectric  7 . Although there is a difference in the transverse (spanwise) structure of the plasma between half-cycles of the discharge, as shown in  FIGS. 2   e  and  2   f , the lateral (chordwise) extent and development of the plasma is essentially the same. A surface plot of the light emission of the plasma as seen by PMT  30  is shown in  FIG. 2   i.    
         [0049]    Referring to  FIG. 3 , the plasma actuator  1  may also be modeled as an electric circuit  100 . In the example circuit  100  the capacitor C 1  represents the capacitance between the exposed electrode  5  and the virtual electrode  13 . The capacitor C 2  represents the capacitance between the virtual electrode  13  and the covered insulated electrode  7 . Because the electrodes  5  and  7  are offset, a capacitance C 3  is included because some field lines connect the electrodes  5  and  7  directly. The capacitance C 3  provides a parallel path for additional displacement current in the circuit, but does not affect the discharge. 
         [0050]    Because the chordwise extent of the plasma changes during the discharge, the capacitances C 1  and C 2  are represented as variable. Therefore, for purposes of this model, the values of C 1  and C 2  are represented as variable. Also, for purposes of this model, the values of C 1  and C 2  may be considered as average capacitances that depend on the amplitude of the applied AC voltage  11 . The plasma is represented as a resistor R 1  because it is the single dissipative element in the circuit. The plasma does not exist during the entire discharge and is thus represented as a variable value as well. When the absolute value of the potential difference falls below another threshold, the discharge quenches and the resistance R 1  returns to its open circuit value. The application of the AC voltage  11  to the plasma actuator  1  allows the discharge to be sustained. 
         [0051]    The power dissipated by the plasma actuator  1  and the maximum extent of the plasma discharge as a function of the frequency of the applied AC voltage are shown in  FIGS. 4   a  and  4   b , respectively. As modeled by the circuit of  FIG. 3 ,  FIGS. 4   a  and  4   b  indicate that an optimum frequency exists for peak plasma power. The existence of the optimum frequency allows the width of the covered, insulated electrode  7  to be reduced. For example, as shown in  FIGS. 4   a  and  4   b , a width of 12 mm is required for a 20 kV voltage applied at 6 kHz. However, for the same 20 kV voltage, the same plasma power discharge may be obtained if the voltage is applied to a 6 mm electrode at 20 kHz. This allows the width of the covered, insulated electrode  7  to be reduced 50%, i.e. from 12 mm to 6 mm. Reducing the width of the covered, insulated electrode  7  allows more dense packing of the actuators to the surface  3  in an array, while using plasma actuators in an array provides a linear additive effect. However, the size of each plasma actuator is typically directly related to the volume of the plasma it produces, thus the chordwise length of the plasma actuator cannot exceed the maximum extent of the plasma for actuators used in an array to prevent any overlapping effects. 
         [0052]    As discussed above, the spatial structure of the plasma discharge is asymmetric. To determine the effects of this asymmetry, two different asymmetric voltage waveforms, which are mirror images of each other, may be applied to the plasma actuator  1 . In one instance, a positive sawtooth waveform, having a large positive slope and a smaller negative slope, was applied to the plasma actuator  1 . In another instance, a negative sawtooth waveform, having a large negative slope and a smaller positive slope, was applied to the plasma actuator  1 . The positive and negative sawtooth voltage and current waveforms are shown in  FIGS. 5   a  and  5   b , respectively. 
         [0053]      FIGS. 5   c  and  5   d  illustrate the light emission from the plasma in the case of the positive sawtooth waveform and the negative sawtooth waveform, respectively. Although the light emissions would appear to have generally the same shape, it is clear from the figures that the negative going portion of the waveform, as shown by point (b) in  FIG. 5   c  and by point (a) in  FIG. 5   d , produces the more uniform discharge. This is consistent with the asymmetry of the plasma discharge discussed above. The positive-going portions of the waveform, as shown by point (a) in  FIG. 5   c  and by point (b) in  FIG. 5   d , produces an irregular discharge, as discussed above with respect to  FIG. 2   d.    
         [0054]    The plasma actuator&#39;s effectiveness may be determined by measuring the thrust it produces in initially still air. To measure the thrust, the actuator  1  may be mounted on a lever arm (not shown) and the thrust it produces measured on a mass balance at the opposite end of the lever arm.  FIG. 5   e  shows an example plot of thrust versus dissipated power for the positive and negative sawtooth waveforms. As shown in the figure, the positive sawtooth waveform, which has a higher negative-going duty cycle and produces a more diffuse plasma for a greater fraction of the discharge cycle, produces a greater thrust than the negative sawtooth waveform. The negative sawtooth waveform produces a more irregular plasma for a greater fraction of the discharge cycle and is less efficient in coupling momentum into the airflow for a comparable dissipated power. This result disproves the theory that the operation of the plasma actuator may be primarily attributable to the bulk heating of the air. 
         [0055]    Referring now to  FIG. 3 , the power dissipation as a function of the amplitude of the applied voltage is consistent with the form and structure of the plasma and its discharge as discussed above. When the plasma ignites, effectively shorting out the capacitor C 1 , it forms part of a voltage divider. The impedance Z 2  of the other element of the voltage divider, i.e. the capacitor C 2 , depends on the frequency of the applied waveform, Z 2 =−i/ωC 2 . For a fixed frequency, the power dissipated would go as V AC   2 , if C 2  is constant, wherein V AC  is the applied voltage. Referring to  FIG. 5   f , the power dissipated in the plasma goes approximately as V AC   7/2 . 
         [0056]    The results shown in  FIG. 5   f  are consistent with one or both of two situations: (1) the average capacitance of the capacitor C 2  increases with increasing applied voltage; and/or 2) the average resistance of the resistor R 1  decreases with increasing applied voltage. As discussed above with respect to  FIG. 2   h , the higher the applied voltage, the faster the plasma discharge spreads along the surface of the dielectric  7 . Therefore, the average area of the virtual electrode  13  increases with increasing applied voltage with a corresponding increase of the capacitance of the capacitor C 2  in the model shown in  FIG. 3 . 
         [0057]    Referring to  FIGS. 5   g  and  5   h , particle image velocimetry (PIV) measurements of the velocity induced in the air by the plasma actuator  1 , shows that the velocity imparted to the flow also goes approximately as V AC   7/2 . This result indicates a direct proportionality between the electrical power dissipated in the actuator and the velocity induced in the air. The efficiency of the momentum coupling may be controlled by interactions at the edge of the exposed electrode  5 .  FIG. 5   g  shows the induced velocity for a square waveform applied voltage and  FIG. 5   h  shows the induced velocity for a triangle waveform applied voltage. The results shown in  FIGS. 5   g  and  5   h  indicate that the proportionality of the induced voltage to V AC   7/2  applies irrespective of waveform shape. 
         [0058]    As discussed above, the use of multiple actuators provides a linear additive effect, i.e. the velocity increase of multiple actuators is additive. Referring to  FIG. 5   i , for an applied voltage, two actuators placed one behind the other provides more than twice the velocity increase of a single actuator alone. 
         [0059]    Airflow separation around a 5 inch diameter cylinder may be smoothed out as shown in  FIGS. 5   j  and  5   k  using plasma actuators. This smoothing may reduce drag by approximately close to 90%. The present disclosure applies this principal to ground vehicles to reduce drag while increasing fuel mileage. 
         [0060]    In the disclosed example, the plasma actuator  1  may be used on a vehicle  200 , such as for example, a Class-8, 18-wheel tractor-trailer rigs as shown in  FIG. 6   a . While the present disclosure describes the application of the plasma actuator  1  to a class-8 truck, it will be appreciated that the vehicle may be any suitable vehicle, such as for instance, a passenger car, bus, van, SUV, pick-up truck, high performance vehicle, or other similar vehicle. In this example, the vehicle  200  is a large, long range rig designed to deliver cargo over local and interstate highway systems and to provide rapid movement of goods where needed from cities, ports, locations of manufactured goods and wholesale distribution points. When conditions allow, these vehicles may cruise from 50 to 70 miles per hour (MPH) non-stop for long distances. For the past 25 years, while passenger cars and small trucks have typically obtained an increase in gasoline mileage, these example class-8 rigs have averaged between approximately 5.5 to 6.5 miles per gallon. As shown in  FIGS. 6   b  and  6   c , there are areas on these rigs where airflow separations and interferences result in significant drag penalties. Accordingly to some studies, on average two-thirds of the power required to cruise one of these rigs at 70 MPH is the result of overcoming aerodynamic drag. Therefore, a significant reduction in that drag could result in large reductions in fuel consumption. 
         [0061]      FIG. 7   a  shows a plan view of an aft section  700  of the vehicle  200 , (e.g. a class-8 trailer) as it is today with a typical airflow  720  depicted showing large separated areas on the back surface of the vehicle. In essence, the airflow  720  cannot make the sharp turn typical of the vehicle  200  and thus separates. This separation causes strong vortices  730  to form, which contribute significantly to the drag of the vehicle  200  (called base drag) and increases fuel consumption. A fairing  740  as shown in  FIG. 7   b  with a plurality of plasma actuators  750  arrayed in various locations can cause the airflow  720  to adhere to the surface around a corner  760  and along a back surface  780  of the vehicle  200 . In this example, the resulting airflow  720  is smoothed out reducing the wake, and increasing the pressure on the rear surface of the trailer. The aerodynamic performance of the vehicle  200  is thus improved which results in less drag, lower fuel consumption and a reduction in the strength of the wake behind the vehicle  200 . In crosswinds the drag may be even greater, and design manipulation of the plasma actuator  750  may improve the handling of the vehicle  720  while showing improved fuel consumption. 
         [0062]    In this example, the fairing  740  shown in  FIG. 7   b  may be made from any suitable material and coupled to the vehicle  720  in such a way to open easily and move out of the way, allowing in the instance of a truck, rapid access to the trailer doors loading and unloading. For instance, the opened fairings  740  may lie alongside the sides of the vehicle  200  like the doors to allow close parking between vehicles  200  at, for example, loading docks or the like. The plasma actuators  750  may be bonded, adhered, laminated, or otherwise secured to the surface of the fairing  740  or recessed in the fairing  740  so that the exposed electrode  5  is flush with the aerodynamic surface of the fairing  740 . The fairing  740  may be painted with suitable paint such as a non-metallic paint, to further protect the actuators  5 , 7  from debris or damage from rough handling. The arrangement of the plasma actuators  750  induces a velocity component in the downstream direction D to inhibit flow separation over the fairing  740 . Each plasma actuator  750 , in this example, is placed just prior to the location where the airflow  720  would naturally separate if the plasma actuators  750  were not present. In one example, during braking of the vehicle  200 , when increased drag actuator  750  may be an advantage, the plasma may be turned off allowing separation of the airflow  720  to occur and drag to increase, thus helping to slow the vehicle. 
         [0063]    The fairing  740  arrangement as tested in this example shows the effect of the plasma actuators  750  on the airflow  720 . In one test, smoke is introduced into the airflow  720  to provide visualization of the airflow  720 . A two-dimensional model of the vehicle  200  and the corner  760 , shown in  FIGS. 8   a  and  8   b  illustrates the impact of the plasma actuator  750  on the airflow  720 . Specifically,  FIG. 8   a  shows a radius airflow  820  with no active plasma actuator  750 .  FIG. 8   b  shows an airflow  825  with the plasma actuator  750  operating at 28.7 kV. Data collected and graphed at  FIG. 9  shows that with one plasma actuator  750 , the flow separation point moved from approximately 37 to approximately 53 degrees around the 4.1 inch radius corner  760 . With a 2.5 inch radius corner (not shown) the flow separation moved from approximately 21 to approximately 52 degrees with one plasma actuator  750 , an increase in flow attachment of approximately 31 degrees. It will be appreciated that with multiple actuators  750 , major flow changes may be expected, reducing the momentum drag and enhancing the fuel efficiency of the vehicle  200 . 
         [0064]      FIG. 9  shows the results of the early testing using all three different radii in a wind tunnel. The data indicate that the separation angle is little affected by velocity, but greatly affected by the radius of the corner  760  and the voltage as applied to the plasma actuator  750  stated above. Additionally, the separation angle is more sensitive to voltage as the radius decreases. Significant delay in the separation angle can be seen at the higher voltages. Pressure data taken in the wake of the model showed significant reduction in momentum drag at the higher separation angles. This data demonstrates that plasma flow control can reduce the drag of the vehicle  200 . 
         [0065]    Other locations on the vehicle  200  also show separation which contributes to drag. In the example of a class-8 truck, the gap between the tractor and the trailer contributes a considerable percentage of the overall drag. The Department of Energy suggests it is also about one-third of the total. The use of plasma actuator to reduce drag of the rear of the example vehicle  200  may be applied to the gap of the vehicle as well. For example, in a class-8 truck, the airflow hitting the front of the trailer may be directed such that treatment at the trailer with fairings and plasma actuators would clean up the airflow and reduce the drag of the gap considerably. In this instance, the front of the trailer may be treated with a fairing and/or plasma actuator to cause the airflow to remain attached along the trailer sides, thus providing drag reduction. Still other areas under the vehicle  200  and around the sides may benefit from the use of plasma actuators to further reduce drag and reduce side forces caused by crosswinds, to reduce power, and to provide some control power relief for vehicles in high winds. 
         [0066]    Although certain example methods and apparatus have been described herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus and articles of manufacture fairly falling within the scope of the appended claims either literally or under the doctrine of equivalents.