it will be readily understood that the components of the present invention , as generally described and illustrated in the drawings herein , could be arranged and designed in a wide variety of different configurations . thus , the following more detailed description of the embodiments of the system and method of the present invention , as represented in the drawings , is not intended to limit the scope of the invention , as claimed , but is merely representative of various embodiments of the invention . the illustrated embodiments of the invention will be best understood by reference to the drawings , wherein like parts are designated by like numerals throughout . this patent application hereby incorporates by reference u . s . pat . no . 5 , 301 , 900 issued apr . 12 , 1994 to groen et al ., u . s . pat . no . 1 , 947 , 901 issued feb . 20 , 1934 to j . de la cierva , and u . s . pat . no . 2 , 352 , 342 issued jun . 27 , 1944 to h . f . pitcairn . referring to fig1 , an aircraft 10 includes a fuselage 12 defining a cabin for carrying an operator , passengers , cargo , or the like . the fuselage 12 may include one or more fixed wings 14 shaped as airfoils for providing lift to the aircraft . the wings 14 may be configured such that they provide sufficient lift to overcome the weight of the aircraft 10 only at comparatively high speeds inasmuch as the aircraft 10 is capable of vertical takeoff and landing ( vtol ) and does not need lift from the fixed wings 14 at low speeds , e . g . below 50 mph or even 100 mph upon taking off . in this manner , the wings 14 may be made smaller than those of fixed wing aircraft requiring a high velocity takeoff , which results in lower drag at higher velocities . in some embodiments the wings 14 provide sufficient lift to support at least 50 percent , preferably 90 percent , of the weight of the aircraft 10 at air speeds above 200 mph . control surfaces 16 may secure to one or both of the fuselage 12 and wings 14 . for example a tail structure 18 may include one or more vertical stabilizers 20 and one or more rudders 22 . the rudders 22 may be adjustable as known in the art to control the yaw 24 of the aircraft 10 during flight . as known in the art , yaw 24 is defined as rotation about a vertical axis 26 of the aircraft 10 . in the illustrated embodiment , the rudders 22 may comprise hinged portions of the vertical stabilizers 20 . the tail structure 18 may further include a horizontal stabilizer 28 and an elevator 30 . the elevator 30 may be adjustable as known in the art to alter the pitch 32 of the aircraft 10 . as known in the art , pitch 32 is defined as rotation in a plane containing the vertical axis 26 and a longitudinal axis 34 of the fuselage of an aircraft 10 . in the illustrated embodiment , the elevator 30 is a hinged portion of the horizontal stabilizer 28 . in some embodiments , twin rudders 22 may be positioned at an angle relative to the vertical axis 26 and serve both to adjust the yaw 24 and pitch 32 of the aircraft 10 . the control surfaces 16 may also include ailerons 36 on the wings 14 . as known in the art , ailerons 36 are used to control roll 38 of the airplane . as known in the art , roll 38 is defined as rotation about the longitudinal axis 34 of the aircraft 10 . lift during vertical takeoff and landing and for augmenting lift of the wings 14 during flight is provided by a rotor 40 comprising a number of individual blades 42 . the blades are mounted to a rotor hub 44 . the hub 44 is coupled to a mast 46 which couples the rotor hub 44 to the fuselage 12 . the rotor 40 may be selectively powered by one or more engines 48 housed in the fuselage 12 , or adjacent nacelles , and coupled to the rotor 40 . in some embodiments , jets 50 located at or near the tips of the blades 42 power the rotor 40 during takeoff , landing , hovering , or when the flight speed of the aircraft is insufficient to provide sufficient autorotation to develop needed lift . referring to fig2 , while still referring to fig1 , in the illustrated embodiment , the engines 48 may be embodied as jet engines 48 that provide thrust during flight of the aircraft . the jet engines 48 may additionally supply compressed air to the jets 46 by driving a bypass turbine 62 or auxiliary compressor . air compressed by the bypass turbine 62 may be transmitted through ducts 54 to a plenum 56 in fluid communication with the ducts 54 . the plenum 56 is in fluid communication with the mast 46 that is hollow or has another passage to provide for air conduction . a mast fairing 58 positioned around the mast 46 may provide one or both of an air channel and a low drag profile for the mast 46 . the mast 46 or mast fairing 58 is in fluid communication with the rotor hub 44 . the rotor hub 44 is in fluid communication with blade ducts 60 extending longitudinally through the blades 42 to feed the tip jets 50 . referring to fig3 a - 3c , rotation of the rotor 40 about its axis of rotation 72 occurs in a rotor disc 70 that is generally planar but may be contoured due to flexing of the blades 42 during flight . in general , the rotor disc 70 may be defined as a plane in which the tips of the blades 42 travel . inasmuch as the blades 42 flap cyclically upward and downward due to changes in lift while advancing and retreating , the rotor disc 70 is angled with respect to the axis of rotation when viewed along the longitudinal axis 34 , as shown in fig3 a . referring to fig3 b , the angle 74 of the rotor disc 70 , relative to a flight direction 76 in the plane containing the longitudinal axis 34 and vertical axis 26 , is defined as the angle of attack 74 or rotor disk angle of attack 74 . for purposes of this application , flight direction 76 and air speed refer to the direction and speed , respectively , of the fuselage 12 of the aircraft 10 relative to surrounding air . in autogyro systems , the angle of attack 74 of the rotor disc 70 is generally positive in order to achieve autorotation of the rotor 40 , which in turn generates lift . referring to fig3 c , the surfaces of the blades 42 , and particularly the chord of each blade 42 , define a pitch angle 78 , or blade angle of attack 78 , relative to the direction of movement 80 of the blades 42 . in general , a higher pitch angle 78 will result in more lift and higher drag on the blade up to the point where stalling occurs , at which point lift has declined below a value necessary to sustain flight . the pitch angle 78 of the blade 42 may be controlled by both cyclic and collective pitch control as known in the art of rotary wing aircraft design . referring to fig4 and 5 , while continuing to refer generally to fig1 - 11 , a system for autorotation may include a rotor system 70 having a mast 72 about which , or with which , rotor blades 74 rotate . each of the blades 74 may have a leading edge 75 a and trailing edge 75 b , on an airfoil 76 or wing 76 portion . for example , a blade 74 may include various attachment mechanisms , individual blade pitch controls , and so forth . ultimately , however , the autorotating of the blades 74 depends on the airfoil 76 , a portion of which operates as a windmill . moreover , the aircraft load 77 or weight 77 of the fuselage and cargo of an aircraft must be opposed by a lift force 78 , commonly simply referred to as lift 78 . accordingly , the airfoil 76 operates according to the bernoulli principles . thus , in flight , the load 77 or weight 77 represented by an aircraft must be opposed by the lift 78 provided by the wings 76 or the rotor blades 74 . in one embodiment of an aircraft in accordance with the invention , the aircraft may be augmented with fixed wings that provide lift in a more aerodynamic and efficient manner at high speeds , and particularly at high advance ratios . in such an embodiment , the rotor system 70 may actually be unloaded such that it does not provide any substantial lift . one benefit for the rotor system 70 not providing lift is that the drag that would have to be sustained in order to provide lift may be eliminated . thus , the blades 74 may be turned to be effectively flat , and not supporting any of the load 77 . however , in order to maintain autorotation in such an embodiment , a drive system 80 is needed to maintain rotation . in accordance with the invention , a drive system 80 may include a top flap 82 and a bottom flap 84 . the top flap and bottom flap may extend along as much of the length of the blades 74 as is necessary to provide sufficient area to provide the autorotating power to drive the blades 74 in autorotation . thus , the top flap 82 and bottom flap 84 may be a matched set that selectively move between closed positions 86 , 88 , respectively , in which the two flaps 82 , 84 provide a suitable trailing edge 75 b for the airfoil 76 . thus , in the closed position 86 , the top flap 82 is in contact with the bottom flap 84 , also in its closed position 88 . more correctly , these closed positions 86 , 88 may be thought of as the closed , camber - neutral positions . for example , each of the top flap 82 and the bottom flap 84 may conceivably be moved in the same direction , and come to a position of closure adding camber to the airfoil 76 . referring to fig6 and 7 , while continuing to refer to fig4 - 5 and to fig1 - 11 generally , a drive system 80 on an airfoil 76 of a blade 74 of a rotor system 70 may encounter a reverse direction 90 of airflow . this is explained hereinabove with respect to retreating blades 74 at high advance ratios . the direction 92 of flight of an aircraft may be thought of as moving into still air , relative velocity rendering it an airstream . accordingly , the direction of flight 92 results in certain anomalies with respect to the shape of the airfoil 76 . in general , the direction of airflow 90 is reversed when the aircraft is traveling at a suitable speed in the direction of flight 92 , and the rotation of the blade 74 or blades 74 that are on the retreating side , moving in the reverse flow direction 90 are moving at a speed that is effectively less than the speed in the direction 92 of flight . in such an environment , a retreating blade experiences a reversed flow direction 90 in which incoming airflow passes from the trailing edge 75 b toward the leading edge 75 a . in flight , an autorotating aircraft has a rotor system 70 that rotates the blade 74 about an axis 94 of rotation . typically , for the descriptions herein , the direction 96 of rotation of the blades 74 will be counterclockwise as illustrated . in this configuration , a region 98 of reversed flow exists , for any trailing edge 75 b or any portion thereof along the length of the blade 74 at which the net forward speed in the direction of flight 92 exceeds the retreating speed of that portion of the plane in the reverse direction 90 . thus , the shape of the reverse flow region 98 varies somewhat with the speed of the aircraft in the direction of flight 92 , and the net linear speed of a trailing edge 75 b of a blade 74 opposite thereto . the rotor disk 100 represents the sweep 100 of the blade 74 of a rotor system 70 . accordingly , the region 102 of positive flow or positive leading edge flow may be thought of as the conventional experience of a blade 74 , or the airfoil 76 of such a blade 74 , advancing into the airstream by its leading edge first . however , the region 98 represents that portion where the trailing edge of a retreating blade 74 is first to encounter the airstream , and the flow is in the reverse direction 90 . thus , actuators operating to pivot the flaps 82 , 84 about their respective pivots 104 , may alter the effective drag near the trailing edge 75 b of the airfoil 76 . referring to fig8 - 11 , in one embodiment , the flaps 82 , 84 may act in concert both moving in the same direction . for example , in fig8 , both the flaps 82 , 84 are positioned in a downward orientation . accordingly , the camber provides more lift , and more drag . likewise , the upper 82 and the lower flap 84 may be positioned both in the upper position in order to provide an opposite effect . referring to fig9 - 11 , in general , an upper surface 106 and lower surface 108 of an airfoil 76 may define a chord 110 or effective airfoil length 110 . similarly , the relative thickness 112 of the airfoil 74 will have a direct effect on drag . the chord 110 and thickness 112 may be designed according to suitable practice as engineered in the art . meanwhile , implementation of the pivots 104 in which the flaps 82 , 84 pivot results in respective radii 114 , 116 for the two flaps 82 , 84 . thus , the trailing edge 75 b of each of the flaps 82 , 84 need not necessarily align . in the camber position of fig1 , a slight mismatch in the contact area would result in the trailing edge 75 b on the lower flap 84 representing the actual final trailing edge of the airfoil 76 . where the camber is reversed , then the trailing edge 75 b of the upper flap 82 would represent the trailing edge of the airfoil 76 . meanwhile , the configuration of fig9 represents a camber - neutral configuration of the airfoil 76 . the configuration of fig1 represents the maximum drag position in the reverse flow direction 90 . here , the trailing edges 75 b of the upper 82 and lower flap 84 are opened in opposite directions in order to maximize drag on the retreating blade 74 in reverse flow . thus , maximum power is imparted to the blades 74 of the rotor system 70 by the reverse air flow 90 . some of the benefits of the system are that upon rotation into the region 102 of positive edge flow , the flaps 82 , 84 may be moved to the camber neutral position of fig9 , and thus minimize drag of the airfoil 76 advancing into the air in the direction 92 of flight . thus , during a rotation , the operation of the upper flap 82 and lower flap 84 may be optimized in order to provide the appropriate drag for autorotative loading on retreating blades 74 power , and the appropriate , minimized drag on the advancing blades 74 of the rotor system 70 . the present invention may be embodied in other specific forms without departing from its spirit or essential characteristics . the described embodiments are to be considered in all respects only as illustrative , and not restrictive . the scope of the invention is , therefore , indicated by the appended claims , rather than by the foregoing description . all changes which come within the meaning and range of equivalency of the claims are to be embraced within their scope .