Method and apparatus for mitigating trailing vortex wakes of lifting or thrust generating bodies

Abstract

Disclosed are methods and apparatuses for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface geometries promotes vortex-mixing of high and low flow fluids. The methods and apparatuses can be combined with various drag reduction techniques, such as the use of riblets of various types and/or compliant surfaces (passive and active). Such combinations form unique structures for various fluid dynamic control applications to suppress transiently growing forms of boundary layer disturbances in a manner that significantly improves performance and has improved control dynamics.

I claim: 
     
         1 . A method for reducing aerodynamic or hydrodynamic drag by mitigating formation of concentrated wake vortex structures, the method comprising:
 applying and/or incorporating at least one three-dimensional contour shaped surface into and/or onto one or more lifting and/or thrust-generating bodies, airfoils, and/or other surfaces.   
     
     
         2 . The method of  claim 1 , wherein the one or more lifting and/or thrust-generating bodies and/or other surfaces comprise one or more fan blade surfaces. 
     
     
         3 . The method of  claim 2 , wherein the fan blade surfaces are located on either an aircraft or watercraft. 
     
     
         4 . The method of  claim 2 , wherein the at least one three-dimensional contour shaped surface promotes vortex-mixing of high and low flow fluids on the one or more fan blade surfaces. 
     
     
         5 . The method of  claim 1 , wherein the applying and/or incorporating is performed on a trailing edge, a leading edge, and/or across a surface of the one or more lifting and/or thrust-generating bodies. 
     
     
         6 . The method of  claim 5 , wherein the at least one three-dimensional contour shaped surface comprises a scallop-shaped surface. 
     
     
         7 . The method of  claim 6 , wherein the scallop-shaped surface has a shape that varies across a trailing edge and/or leading edge of a surface. 
     
     
         8 . The method of  claim 7 , wherein the shape varies from the leading edge of the surface to the trailing edge. 
     
     
         9 . The method of  claim 6 , wherein the scallop-shaped surface enables a mixing of a lower fluid stream and an upper fluid stream flowing across the one or more lifting or thrust-generating bodies such that a position of the mixing is varied across the trailing edge. 
     
     
         10 . The method of  claim 1 , further comprising:
 incorporating at least one riblet and/or at least one compliant surface into the one or more lifting and/or thrust-generating bodies for drag reduction, wherein the at least one riblet and/or the at least one compliant surface combines with the at least one three-dimensional contour shaped surface to form at least one unique structure.   
     
     
         11 . The method of  claim 10 , wherein the at least one unique structure is configured to suppress transiently growing forms of boundary layer disturbances, thereby resulting in improved performance and control dynamics of the one or more lifting and/or thrust-generating bodies and/or other surfaces. 
     
     
         12 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface is applied to the one or more lifting and/or thrust-generating bodies and/or other surfaces, and wherein the one or more lifting and/or thrust-generating bodies and/or other surfaces comprise engine structures and/or blade structures of an aircraft jet engine. 
     
     
         13 . The method of  claim 12 , wherein the application of the at least one three-dimensional contour shaped surface into the one or more lifting and/or thrust-generating bodies or other surfaces results in improved vortex mixing within the aircraft jet engine. 
     
     
         14 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface comprises one or more structural shells or volumes and connected or related appendages of the one or more structural shells or volumes. 
     
     
         15 . The method of  claim 14 , wherein the one or more structural shells or volumes are combined with rigid and/or compliant material in one or more parametric dimensions, wherein the one or more parametric dimensions correspond to MEMS devices. 
     
     
         16 . The method of  claim 14 , wherein the one or more structural shells or volumes comprise mesh curves, and wherein the mesh curves are spiral-shaped. 
     
     
         17 . The method of  claim 16 , wherein the mesh curves are configured to make more efficient the provision needed for a local density of the mesh curves in way of potentially shape-ambiguous inflections within intervals. 
     
     
         18 . The method of  claim 16 , wherein the mesh curves vary in width and thickness to accommodate local surface curvature at each intersection adjacent to each of the mesh curves. 
     
     
         19 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface is applied at a wing tip of an aircraft. 
     
     
         20 . The method of  claim 19 , wherein the application of the at least one three-dimensional contour shaped surface at the wing tip of the aircraft reduces concentration and duration of wake vortex structures at the wing tip. 
     
     
         21 . The method of  claim 1 , wherein the applying and/or incorporating at least one three-dimensional contour shaped surface comprises applying the at least one three-dimensional contour shaped surface on a structure selected from the group consisting of: rotors, rotating devices, rotary devices, stabilators, flaps, micro-flaps, slats, elevons, flaperons, ailerons, elevators, rudders, trailing edge tabs, miniature trailing edge effectors, micro flaps, field generators, slits, body rakes, wings, sails, trailing edge tabs, miniature trailing edge effectors, helicopter blades, tilt-rotor blades, waterjet impellers, propellers, mixers, turbines, blades, fans, and combinations thereof. 
     
     
         22 . The method of  claim 1 , wherein the applying and/or incorporating at least one three-dimensional contour shaped surface comprises applying the at least one three-dimensional contour shaped surface to an article of manufacture selected from the group consisting of: an aircraft, a motorcycle, an automobile, a truck, a train, a section of a tractor trailer, a submarine, a hydrofoil, an amphibious vehicle, a bow-plane, a ship, a ship hull, a missile, a torpedo, a windsurfer, a barge, a jet ski, a sail, a surfboard, a sled, a ski, a piece of athletic equipment, a piece of athletic apparel, a building, a bridge, an oil rig, a pipeline, a heat exchanger, and combinations thereof. 
     
     
         23 . The method of  claim 22 , wherein the at least one three-dimensional contour shaped surface is configured to reduce aerodynamic drag. 
     
     
         24 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface comprises individual contours, and further comprising:
 changing, via one or more MEMS devices, one or more of the individual contours during operation of the one or more lifting and/or thrust-generating bodies.   
     
     
         25 . The method of  claim 24 , wherein the changed one or more individual contours reduces drag caused by wake turbulence. 
     
     
         26 . The method of  claim 24 , wherein the changed one or more individual contours results in formation of counter-rotating vortices centered around the individual contours and allows for vortex-mixing of low and high fluid velocity fields to generate smaller wake vortex structures along a span of the one or more lifting and/or thrust-generating bodies. 
     
     
         27 . The method of  claim 24 , wherein the one or more MEMS devices are configured to control fluid flow in order to reduce vortex-induced drag via vortex mixing. 
     
     
         28 . The method of  claim 1 , further comprising:
 placing one or more holes and/or mesh on the one or more lifting and/or thrust-generating bodies.   
     
     
         29 . The method of  claim 28 , wherein the placing of the one or more holes and/or mesh is configured to generate vortex mixing and to result in reduced vortex-induced drag. 
     
     
         30 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface comprises one or more holes and/or a compliant wall that are configured to allow fluid flow to enter, thereby resulting in reduced localized pressure. 
     
     
         31 . The method of  claim 1 , further comprising:
 integrating one or more electric and/or magnetic fields into the at least one three-dimensional contour shaped surface; and/or   integrating one or more smart materials into the at least one three-dimensional contour shaped surface, wherein the one or more smart materials is selected from the group consisting of:   shape memory polymers, shape memory composites, dynamic composites, dynamic syntactic foams, shape memory alloys, piezoelectric actuators, magneto-rheological fluids and solids, self-healing polymers and coatings, and combinations thereof,   wherein the one or more electric and/or magnetic fields and/or the one or more smart materials are configured to create morphing flexible contour shaped surfaces and/or structures.   
     
     
         32 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface is varied in an oscillatory fashion. 
     
     
         33 . The method of  claim 32 , wherein the variation in the oscillatory fashion is configured to affect one or more parameters of vortex production. 
     
     
         34 . The method of  claim 32 , further comprising:
 utilizing spatial averaging for an along-beam or span-wise direction of the one or more lifting and/or thrust-generating bodies.   
     
     
         35 . The method of  claim 1 , further comprising:
 applying one or more oscillatory structures on the one or more lifting and/or thrust-generating bodies.   
     
     
         36 . The method of  claim 35 , wherein the applying of the one or more oscillatory structures generates smaller vortices of periodic, time-varying strength along a span and/or a surface of the one or more lifting and/or thrust-generating bodies, thereby promoting de-intensification of the wake vortex structures. 
     
     
         37 . The method of  claim 35 , wherein the one or more oscillatory structures comprise a periodic geometric form. 
     
     
         38 . The method of  claim 37 , wherein the one or more oscillatory structures comprise a sinusoidal form. 
     
     
         39 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface comprises one or more denticle-shaped portions. 
     
     
         40 . The method of  claim 39 , wherein the one or more denticle-shaped portions is similar in shape to dermal denticles of sharks. 
     
     
         41 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface comprises a surface with one or more serrations and/or saw-toothed serrations. 
     
     
         42 . A method comprising:
 combining at least one riblet and/or at least one compliant surface with a trailing edge of one or more lifting and/or thrust-generating bodies, airfoils, and/or other surfaces, thereby producing at least one contour-shaped surface on the one or more lifting and/or thrust-generating bodies, airfoils, and/or other surfaces, wherein the at least one contour-shaped surface varies across the trailing edge.   
     
     
         43 . The method of  claim 42 , wherein the at least one contour-shaped surface varying across the trailing edge thereby reduces wake vortex perturbations along the one or more lifting and/or thrust-generating bodies. 
     
     
         44 . The method of  claim 42 , wherein the at least one contour-shaped surface is configured to promote chord-wise fluid flow and to enable mixing of a lower fluid stream and an upper fluid stream passing over the one or more lifting and/or thrust-generating bodies, such that time and position of the mixing is varied across a span of a trailing edge of the one or more lifting and/or thrust-generating bodies, thereby reducing size and duration of trailing wake vortexes generated by the one or more lifting and/or thrust-generating bodies and/or other surfaces. 
     
     
         45 . The method of  claim 42 , wherein the at least one riblet is selected from the group consisting of: compound riblets, three-dimensional riblets, and geometrically-shaped riblets. 
     
     
         46 . The method of  claim 45 , wherein the geometrically-shaped riblets comprise a shape selected from the group consisting of: a pyramid, a rectangle, a compound rectangle, a tetrahedron, a compound tetrahedron, and combinations thereof. 
     
     
         47 . The method of  claim 42 , wherein the at least one riblet is configured to excite short-wavelength vortex instabilities, thereby resulting in an accelerated delay of trailing vortices leading to wake breakup and a reduction in total kinetic energy of wake structures formed. 
     
     
         48 . The method of  claim 42 , wherein the at least one contour-shaped surface is configured to allow one or more MEMS devices to be activated. 
     
     
         49 . The method of  claim 48 , wherein the activation of the one or more MEMS devices results in further mitigation of concentrated trailing wake vortex structures generated by the one or more lifting and/or thrust-generating bodies. 
     
     
         50 . The method of  claim 42 , wherein the at least one contour-shaped surface comprises one or more vibrating piezoceramic elements. 
     
     
         51 . The method of  claim 50 , further comprising:
 activating the one or more vibrating piezoceramic elements to further mitigate concentrated trailing wake vortex structures generated by the one or more lifting and/or thrust-generating bodies.   
     
     
         52 . The method of  claim 42 , wherein the at least one contour-shaped surface is selected from the group consisting of: corrugated surfaces, corrugated edges, serrated surfaces, serrated edges, convoluted surfaces, convoluted edges, control surfaces, geometrically irregular surfaces, geometrically irregular edges, and combinations thereof. 
     
     
         53 . The method of  claim 42 , further comprising optimally placing the at least one riblet on the one or more lifting and/or thrust-generating bodies and/or other surfaces to reduce adverse high-speed effects associated with shock waves and flow separation. 
     
     
         54 . The method of  claim 53 , wherein the one or more lifting and/or thrust-generating bodies and/or other surfaces is an aircraft wing. 
     
     
         55 . The method of  claim 42 , further comprising:
 generating a binary boundary layer over the one or more lifting and/or thrust-generating bodies and/or other surfaces by injecting a fluid into a fluid flow boundary layer.   
     
     
         56 . The method of  claim 42 , wherein the at least one contour-shaped surface comprises geometric variations in chord length, wherein the one or more lifting and/or thrust-generating bodies and/or other surfaces comprises an airfoil. 
     
     
         57 . The method of  claim 56 , further comprising:
 designing the geometric variations to produce multiple wake vortices that are smaller in intensity than wake structures generated at a tip region of the airfoil in the absence of the geometric variations.   
     
     
         58 . A method for decreasing drag on surfaces, the method comprising:
 implementing, on a surface, one or more contour shapes that vary across three dimensions of the surface, wherein the surface comprises a lifting and/or thrust-generating surface.   
     
     
         59 . The method of  claim 58 , wherein the one or more contour shapes are configured to generate smaller wake perturbations than the surface. 
     
     
         60 . The method of  claim 58 , wherein time and position of fluid stream mixing is varied across a trailing edge of the surface, thus reducing size and energy of wakes generated from the surface, thereby decreasing drag. 
     
     
         61 . The method of  claim 58 , wherein the fluid stream comprises air and/or water flow, and wherein the surface is located on a structure that is selected from the group consisting of: oil rigs, exhaust pipes, towers, pipe structures, bridges, buildings, and combinations thereof. 
     
     
         62 . The method of  claim 58 , wherein the surface comprises a component present in an aircraft maneuvering and/or control system. 
     
     
         63 . The method of  claim 58 , wherein the one or more contour shapes reduces flutter due to wake vortex-induced oscillations, thereby reducing a rate of wear and cyclic stress associated with the lifting and/or thrust-generating surface. 
     
     
         64 . An apparatus comprising a surface, the surface comprising:
 one or more geometric variations in chord length along a span-wise direction of the surface; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges.   
     
     
         65 . The apparatus of  claim 64 , wherein the one or more corrugated, serrated, convoluted, trailing, geometrically regular, and/or geometrically irregular edges are capable of decreasing drag and/or noise. 
     
     
         66 . The apparatus of  claim 64 , wherein the apparatus is a fan blade. 
     
     
         67 . The apparatus of  claim 66 , wherein the one or more geometric variations produce multiple wake vortices that are smaller in intensity at a tip region of the fan blade than concentrated vortex structures generated when the one or more geometric variations are absent. 
     
     
         68 . The apparatus of  claim 67 , wherein the one or more geometric variations are situated across the span of the fan blade. 
     
     
         69 . The apparatus of  claim 66 , wherein the one or more geometric variations reduce drag and noise by producing multiple wake vortices that are smaller in intensity than the concentrated vortex structures that would be generated at a tip region of the fan blade if the one or more geometric variations were absent. 
     
     
         70 . The apparatus of  claim 66 , wherein the fan blade comprises one or more corrugated, serrated, convoluted, geometrically regular and/or geometrically irregular surface geometry variations. 
     
     
         71 . The apparatus of  claim 66 , wherein the fan blade further comprises, on leading and/or trailing edges of the fan blade, one or more corrugated, serrated, convoluted, geometrically regular and/or geometrically irregular edge geometry variations. 
     
     
         72 . The apparatus of  claim 66 , further comprising one or more geometric portions that reduce wake vortex perturbations along the span of the fan blade. 
     
     
         73 . The method of  claim 35 , wherein applying and/or incorporating at least one three-dimensional contour shaped surface comprises applying the at least one three-dimensional contour shaped surface to one or more rotating or rotary devices selected from the group consisting of mixers, propellers, impellers, turbines, blades, rotors, fans, and combinations thereof. 
     
     
         74 . The method of  claim 73 , wherein the application of the at least one three-dimensional contour shaped surface to the one or more rotating or rotary devices causes reduced drag. 
     
     
         75 . The method of  claim 1 , further comprising putting micro-flaps on the one or more lifting and/or thrust-generating bodies. 
     
     
         76 . The method of  claim 75 , wherein the micro-flaps prevent or reduce vortex-inducted flutter. 
     
     
         77 . The method of  claim 75 , wherein the micro-flaps are on the trailing edge of the one or more lifting and/or thrust-generating bodies. 
     
     
         78 . The method of  claim 1 , further comprising:
 applying and/or incorporating at least one riblet and/or at least one compliant surface into the one or more lifting and/or thrust-generating bodies, wherein the at least one riblet and/or the at least one compliant surface combines with the at least one three-dimensional contour shaped surface to form at least one unique structure.   
     
     
         79 . The method of  claim 78 , further comprising:
 altering the at least one three-dimensional contour shaped surface by dynamically changing one or more physical properties of the at least one three-dimensional contour-shaped surface.   
     
     
         80 . The method of  claim 79 , wherein the one or more physical properties is selected from the group consisting of: geometric curvature, rate of change of curvature, deformation, and combinations thereof. 
     
     
         81 . The method of  claim 79 , wherein the dynamic altering is achieved via one or more compliant walls, one or more shape memory alloys, and/or one or more MEMS actuators. 
     
     
         82 . The method of  claim 39 , wherein the one or more denticle-shaped portions are MEMS devices, further comprising:
 actuating the one or more denticle-shaped portions.   
     
     
         83 . The method of  claim 82 , wherein actuating the one or more denticle-shaped portions comprises actuating the one or more denticle-shaped portions upward into fluid flow, increasing drag, and/or downward out of fluid flow, decreasing drag. 
     
     
         84 . The method of  claim 83 , wherein the actuating results in a change in torque of the one or more lifting and/or thrust-generating bodies and/or other surfaces, thereby causing a directional change of a craft comprising the one or more lifting and/or thrust-generating bodies and/or other surfaces and permitting control of the craft instead of, or in addition to, other control surfaces on the craft. 
     
     
         85 . The method of  claim 84 , wherein the craft is an aircraft or a watercraft. 
     
     
         86 . The method of  claim 24 , further comprising:
 actuating the one or more MEMS devices to generate controlled small-scale turbulence.   
     
     
         87 . The method of  claim 86 , wherein the controlled small-scale turbulence allows for control of drag, thereby resulting in aerodynamic or hydrodynamic control that influences or controls laminar flow. 
     
     
         88 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface is varied and/or variable in one or more of the three dimensions. 
     
     
         89 . The method of  claim 1 , wherein geometry of the at least one three-dimensional contour shaped surface is varied and/or variable across a parameter selected from the group consisting of:
 degree of curvature, rate of curvature, contour shape, degree of twist and/or camber, and combinations thereof.   
     
     
         90 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface is applied to the one or more lifting and/or thrust-generating bodies and/or other surfaces, thereby resulting in improved vortex mixing. 
     
     
         91 . The method of  claim 90 , wherein the improved vortex mixing results in induced smaller wake vortices, the induced smaller wake vortices having a dissipation rate at least an order of magnitude smaller when compared to concentrated wake vortex structures. 
     
     
         92 . The method of  claim 90 , wherein the improved vortex mixing results in reduced energy intensity of wake vortex structures generated. 
     
     
         93 . The method of  claim 90 , further comprising:
 implementing one or more active compliant surfaces and/or passive compliant surfaces on the one or more lifting and/or thrust-generating bodies and/or other surfaces.   
     
     
         94 . The method of  claim 93 , further comprising using the at least one three-dimensional contour shaped surface with the one or more active compliant surfaces and/or passive compliant surfaces to control forces between the one or more lifting and/or thrust-generating bodies and/or other surfaces and at least one other surface. 
     
     
         95 . The method of  claim 94 , wherein the forces are aerodynamic and/or hydrodynamic forces. 
     
     
         96 . The method of  claim 1 , wherein at least one three-dimensional contour shaped surface comprises a dynamic compliant surface, further comprising:
 utilizing the dynamic compliant surface to modify a velocity profile of fluid flow in an adjacent boundary layer.   
     
     
         97 . The method of  claim 96 , wherein the utilizing further comprises using one or more control algorithms and/or one or more sensors. 
     
     
         98 . The method of  claim 96 , wherein the fluid flow velocity profile modification reduces drag in the adjacent boundary layer when the adjacent boundary layer is turbulent. 
     
     
         99 . The method of  claim 96 , wherein the dynamic compliant surface comprises MEMS actuator devices. 
     
     
         100 . The method of  claim 99 , wherein the MEMS actuator devices are driven at one or more frequencies and/or one or more resonances to maximize displacement and thereby maximize effectiveness of the MEMS actuator devices. 
     
     
         101 . The method of  claim 99 , wherein the MEMS actuator devices are arranged into an array. 
     
     
         102 . The method of  claim 101 , wherein the array is constructed of individually addressable piezoelectric cantilevers. 
     
     
         103 . The method of  claim 101 , wherein the array is integrated with riblets and cavities. 
     
     
         104 . The method of  103 , wherein integration with riblets causes formation of counter-rotating vortices centered around each riblet, generating disturbance velocity fields in the adjacent boundary layer when the adjacent boundary layer is laminar. 
     
     
         105 . The method of  claim 104 , wherein the disturbance velocity fields permit increased fluid flow control, thereby resulting in increased flight control and/or drag reduction. 
     
     
         106 . The method of  claim 1 , further comprising:
 applying and/or incorporating one or more MEMS devices at one or more points along a length and/or an edge of the one or more lifting and/or thrust-generating bodies and/or other surfaces.   
     
     
         107 . The method of  claim 106 , wherein the one or more MEMS devices comprises one or more sensors and/or actuators. 
     
     
         108 . The method of  claim 106 , wherein the length is a span length and/or a chord length, and wherein the edge is a trailing edge and/or a leading edge. 
     
     
         109 . The method of  claim 13 , wherein the improved vortex mixing provides noise control and reduces aerodynamic noise. 
     
     
         110 . The method of  claim 60 , wherein the reduction of size and energy of wakes generated from the surface results in improved performance of an aircraft and/or watercraft, and propeller cavitations thereof. 
     
     
         111 . The method of  claim 10 , wherein the incorporation results in fluid flow energy being dissipated through internal damping. 
     
     
         112 . The method of  claim 107 , further comprising:
 applying and/or incorporating, along a length and/or an edge of the one or more lifting and/or thrust-generating bodies and/or other surfaces, one or more electric and/or magnetic fields and/or one or more smart materials.   
     
     
         113 . The method of  claim 112 , wherein the one or more smart materials is selected from the group consisting of: shape memory polymers, shape memory composites, dynamic composites, dynamic syntactic foams, shape memory alloys, piezoelectric actuators, magneto-rheological fluids and solids, self-healing polymers and coatings for creating morphing flexible contour shape surfaces and/or structures, adaptive materials for creating adaptive and/or morphing composite structures, and combinations thereof. 
     
     
         114 . The method of  claim 41 , wherein the surface with one or more serrations and/or saw-toothed serrations is shaped like an owl feather. 
     
     
         115 . The method of  claim 42 , wherein the vortex-mixing improves performance capability of the one or more lifting and/or thrust-generating bodies and/or other surfaces by reducing induced drag. 
     
     
         116 . The method of  claim 42 , the at least one contour-shaped surface comprises one or more shapes having one or more geometric variations. 
     
     
         117 . The method of  claim 116 , wherein the one or more geometric variations is selected from the group consisting of: period of placement, size, rate of curvature change, shape of curvature change, and combinations thereof. 
     
     
         118 . The method of  claim 117 , wherein the one or more geometric variations occurs in one or more of three dimensions along a spanwise direction of the one or more lifting and/or thrust-generating bodies and/or other surfaces. 
     
     
         119 . The method of  claim 42 , wherein the vortex-mixing increases agility and performance envelope, and reduces fuel burn. 
     
     
         120 . The method of  claim 55 , further comprising:
 utilizing one or more nano- and/or micro-scale electromechanical systems to control development of turbulent structures in a binary boundary layer.   
     
     
         121 . The method of  claim 42 , wherein the one or more lifting and/or thrust-generating bodies and/or other surfaces comprises one or more deflectable surfaces. 
     
     
         122 . The method of  claim 64 , wherein the length is a chord length. 
     
     
         123 . A method for reducing wake vortex formation, the method comprising:
 implementing one or more variations in geometric structure of one or more propeller blades or fan blades that produce multiple wake vortices that are smaller in intensity than concentrated wake structures that would be generated at a tip region of the one or more propeller blades or fan blades if the one or more variations in geometric structure were absent.   
     
     
         124 . The method of  claim 123 , wherein the one or more variations reduces propeller blade noise. 
     
     
         125 . The method of  claim 123 , wherein the one or more variations is on a leading edge and/or a trailing edge. 
     
     
         126 . The method of  claim 123 , wherein the one or more variations comprise one or more MEMS devices, one or more riblets, and/or one or more grooves. 
     
     
         127 . The surface of  claim 64 , wherein the surface is that of a propeller blade. 
     
     
         128 . The method of  claim 48 , wherein the one or more MEMS devices are configured to provide aerodynamic and/or hydrodynamic control of one or more forces. 
     
     
         129 . The method of  claim 99 , wherein the MEMS actuator devices are configured to provide aerodynamic and/or hydrodynamic control of one or more forces. 
     
     
         130 . The method of  claim 106 , wherein the one or more MEMS devices are configured to provide aerodynamic and/or hydrodynamic control of one or more forces. 
     
     
         131 . The method of  claim 126 , wherein the one or more MEMS devices are configured to provide aerodynamic and/or hydrodynamic control of one or more forces. 
     
     
         132 . The apparatus of  claim 64 , wherein the one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions and/or one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges comprise one or more portions shaped like an owl feather. 
     
     
         133 . The apparatus of  claim 64 , wherein the one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges comprise one or more portions of a trailing edge shaped like an owl feather. 
     
     
         134 . A method for providing increased control and/or reduced noise of a surface, the method comprising:
 implementing one or more geometric shapes along at least a portion of a surface, wherein the surface comprises areas where said geometric shapes are implemented on the surface and/or a leading edge and/or a trailing edge of the surface.   
     
     
         135 . The method of  claim 134 , wherein the surface is an aerodynamic or hydrodynamic surface. 
     
     
         136 . The method of  claim 135 , wherein the surface is on an apparatus selected from the group consisting of: windmill blades, fan blades, propeller blades, aircraft wings, aircraft control surfaces, helicopter rotor blades, and combinations thereof. 
     
     
         137 . The method of  claim 134 , wherein the one or more oscillating geometric shapes provide passive boundary later control of the leading edge. 
     
     
         138 . The method of  claim 134 , wherein the one or more oscillating geometric shapes generate a plurality of wake vortices along a span of the leading edge that have a lower kinetic energy than concentrated wake vortex structures generated in the absence of the one or more oscillating geometric shapes. 
     
     
         139 . The method of  claim 138 , wherein the one or more oscillating geometric shapes reduce airflow separation due to the plurality of wake vortices permit airflow to remain attached to the surface. 
     
     
         140 . The method of  claim 134 , wherein the one or more oscillating geometric shapes generate a plurality of wake vortices past the trailing edge that are smaller in intensity than wake vortices generated in the absence of the one or more oscillating geometric shapes. 
     
     
         141 . The method of  claim 134 , wherein the one or more oscillating geometric shapes generate a plurality of wake vortices that have a reduced size and a reduced energy at a tip region of the surface than wake vortices generated in the absence of the one or more oscillating geometric shapes. 
     
     
         142 . The method of  claim 134 , wherein the one or more oscillating geometric shapes comprise one or more serrations and/or saw-toothed serrations. 
     
     
         143 . The method of  claim 142 , wherein the one or more serrations and/or saw-toothed serrations are shaped like an owl feather. 
     
     
         144 . The method of  claim 142 , wherein the one or more serrations and/or saw-toothed serrations are shaped like denticles. 
     
     
         145 . A method, comprising:
 applying and/or integrating into a surface:   one or more geometric variations in length along a span-wise direction of the surface; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges.   
     
     
         146 . The apparatus of  claim 66 , wherein the fan blade is located on either an aircraft or watercraft. 
     
     
         147 . The apparatus of  claim 64 , wherein the surface promotes vortex-mixing of high and low flow fluids. 
     
     
         148 . The apparatus of  claim 64 , wherein the one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges is on a trailing edge and/or a leading edge of one or more lifting and/or thrust-generating bodies. 
     
     
         149 . The apparatus of  claim 64 , comprising one or more geometric variations and/or the one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions, wherein the surface is a surface of one or more lifting and/or thrust-generating bodies. 
     
     
         150 . The apparatus of  claim 64 , wherein the surface enables a mixing of a lower fluid stream and an upper fluid stream flowing across one or more lifting and/or thrust-generating bodies such that a position of the mixing is varied across a trailing edge of the one or more lifting and/or thrust-generating bodies. 
     
     
         151 . The apparatus of  claim 64 , further comprising at least one riblet and/or at least one compliant surface. 
     
     
         152 . The apparatus of  claim 151 , wherein the at least one riblet is selected from the group consisting of: compound riblets, three-dimensional riblets, and geometrically-shaped riblets. 
     
     
         153 . The apparatus of  claim 152 , wherein the geometrically-shaped riblets comprise a shape selected from the group consisting of: a pyramid, a rectangle, a compound rectangle, a tetrahedron, a compound tetrahedron, and combinations thereof. 
     
     
         154 . The apparatus of  claim 151 , wherein the at least one riblet is configured to excite short-wavelength vortex instabilities, thereby resulting in an accelerated delay of trailing vortices leading to wake breakup and a reduction in total kinetic energy of wake structures formed. 
     
     
         155 . The apparatus of  claim 151 , wherein the surface is configured to suppress transiently growing forms of boundary layer disturbances, thereby resulting in improved performance and control dynamics of the surface. 
     
     
         156 . The apparatus of  claim 64 , wherein the surface is a surface of one or more structural shells or volumes and/or connected or related appendages of the one or more structural shells or volumes. 
     
     
         157 . The apparatus of  claim 156 , wherein the one or more structural shells or volumes are combined with rigid and/or compliant material in one or more parametric dimensions, wherein the one or more parametric dimensions correspond to MEMS devices. 
     
     
         158 . The apparatus of  claim 156 , wherein the one or more structural shells or volumes comprise mesh curves, and wherein the mesh curves are spiral-shaped. 
     
     
         159 . The apparatus of  claim 64 , wherein the surface is on a structure selected from the group consisting of: rotors, rotating devices, rotary devices, stabilators, flaps, micro-flaps, slats, elevons, flaperons, ailerons, elevators, rudders, trailing edge tabs, miniature trailing edge effectors, micro flaps, field generators, slits, body rakes, wings, sails, trailing edge tabs, miniature trailing edge effectors, helicopter blades, tilt-rotor blades, waterjet impellers, propellers, mixers, turbines, blades, fans, and combinations thereof. 
     
     
         160 . The apparatus of  claim 64 , wherein the surface is on an article of manufacture selected from the group consisting of: an aircraft, a motorcycle, an automobile, a truck, a train, a section of a tractor trailer, a submarine, a hydrofoil, an amphibious vehicle, a bow-plane, a ship, a ship hull, a missile, a torpedo, a windsurfer, a barge, a jet ski, a sail, a surfboard, a sled, a ski, a piece of athletic equipment, a piece of athletic apparel, a building, a bridge, an oil rig, a pipeline, a heat exchanger, and combinations thereof. 
     
     
         161 . The apparatus of  claim 64 , wherein the surface further comprises one or more MEMS devices. 
     
     
         162 . The apparatus of  claim 161 , wherein the surface is on one or more lifting and/or thrust-generating bodies, and wherein the one or more MEMS devices are configured to change at least a portion of the surface during operation of the one or more lifting and/or thrust-generating bodies. 
     
     
         163 . The apparatus of  claim 162 , wherein the changed at least a portion of the surface results in formation of counter-rotating vortices and allows for vortex-mixing of low and high fluid velocity fields to generate smaller wake vortex structures along a span of the one or more lifting and/or thrust-generating bodies, thereby reducing drag caused by wake turbulence. 
     
     
         164 . The apparatus of  claim 161 , wherein the one or more MEMS devices are configured to control fluid flow in order to reduce vortex-induced drag via vortex mixing. 
     
     
         165 . The apparatus of  claim 161 , wherein the surface is configured to allow the one or more MEMS devices to be activated. 
     
     
         166 . The apparatus of  claim 165 , wherein the activation of the one or more MEMS devices results in mitigation of concentrated trailing wake vortex structures generated by one or more lifting and/or thrust-generating bodies. 
     
     
         167 . The apparatus of  claim 64 , wherein the surface comprises one or more holes and/or a compliant wall that are configured to allow fluid flow to enter, thereby resulting in reduced localized pressure. 
     
     
         168 . The apparatus of  claim 64 , wherein the surface further comprises one or more electric and/or magnetic fields and/or one or more smart materials, wherein the one or more smart materials is selected from the group consisting of: shape memory polymers, shape memory composites, dynamic composites, dynamic syntactic foams, shape memory alloys, piezoelectric actuators, magneto-rheological fluids and solids, self-healing polymers and coatings for creating morphing flexible contour shape surfaces and/or structures, adaptive materials for creating adaptive and/or morphing composite structures, and combinations thereof. 
     
     
         169 . The apparatus of  claim 64 , wherein the surface comprises one or more vibrating piezoceramic elements. 
     
     
         170 . The apparatus of  claim 169 , wherein the one or more vibrating piezoceramic elements are configured to mitigate concentrated trailing wake vortex structures generated by one or more lifting and/or thrust-generating bodies. 
     
     
         171 . The apparatus of  claim 64 , wherein the surface comprises a component present in an aircraft maneuvering and/or control system. 
     
     
         172 . The apparatus of  claim 64 , wherein the surface is configured to be altered by dynamically changing one or more physical properties, the one or more physical properties selected from the group consisting of: geometric curvature, rate of change of curvature, deformation, and combinations thereof. 
     
     
         173 . The apparatus of  claim 172 , wherein the dynamic altering is achieved via one or more compliant walls, one or more shape memory alloys, and/or one or more MEMS actuators. 
     
     
         174 . The apparatus of  claim 64 , wherein geometry of the surface is varied and/or variable across a parameter selected from the group consisting of: degree of curvature, rate of curvature, contour shape, degree of twist and/or camber, and combinations thereof. 
     
     
         175 . The apparatus of  claim 64 , wherein the surface further comprises one or more active compliant surfaces and/or passive compliant surfaces. 
     
     
         176 . The apparatus of  claim 64 , the surface comprising:
 one or more geometric variations in length along a span-wise direction of the surface; and/or   one or more corrugated, serrated, and/or convoluted portions; and/or   one or more corrugated, serrated, and/or convoluted edges.   
     
     
         177 . An apparatus for reducing aerodynamic or hydrodynamic drag by mitigating formation of concentrated wake vortex structures, the apparatus comprising:
 at least one three-dimensional contour-shaped surface located on a trailing edge, a leading edge, and/or across a surface of one or more lifting and/or thrust-generating bodies and/or airfoils.   
     
     
         178 . An apparatus comprising a surface, the surface comprising:
 at least one riblet and/or at least one compliant surface on a trailing edge of one or more lifting and/or thrust-generating bodies, airfoils, and/or other surfaces, thereby producing at least one contour-shaped surface on the one or more lifting and/or thrust-generating bodies and/or other surfaces, wherein the at least one contour-shaped surface varies across the trailing edge.   
     
     
         179 . An apparatus for decreasing drag, the apparatus comprising:
 a surface comprising one or more contour shapes that vary across three dimensions of the surface.   
     
     
         180 . An apparatus comprising a surface, the surface comprising:
 one or more repeating variations in length along a span-wise direction of the surface; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges.   
     
     
         181 . An apparatus for promoting chord-wise fluid flow, the apparatus comprising:
 a lifting and/or thrust-generating body and/or an airfoil, comprising one or more structures,   wherein the one or more structures are selected from the group consisting of: grooves, slots, a laminated surface, a composite surface, and combinations thereof.   
     
     
         182 . The apparatus of  claim 181 , wherein the lifting and/or thrust-generating body and/or the airfoil has a three-dimensional contour geometry that varies in at least one of the three dimensions. 
     
     
         183 . The apparatus of  claim 181 , wherein the apparatus is aerodynamic or hydrodynamic, and wherein the lifting and/or thrust-generating body and/or the airfoil is either stationary or rotary. 
     
     
         184 . The apparatus of  claim 183 , wherein the lifting and/or thrust-generating body and/or the airfoil has reduced drag and noise when traveling through a fluid. 
     
     
         185 . A method for promoting chord-wise fluid flow, the method comprising:
 incorporating one or more structures into a lifting and/or thrust-generating body and/or an airfoil,   wherein the one or more structures are selected from the group consisting of: grooves, slots, a laminated surface, a composite surface, and combinations thereof.   
     
     
         186 . The method of  claim 185 , wherein the lifting and/ or thrust-generating body and/or the airfoil has a three-dimensional contour geometry that varies in at least one of the three dimensions. 
     
     
         187 . The method of  claim 185 , wherein the lifting and/or thrust-generating body and/or the airfoil is disposed in an aerodynamic or hydrodynamic apparatus, and wherein the lifting and/or thrust-generating body and/or the airfoil is either stationary or rotary. 
     
     
         188 . The method of  claim 187 , wherein the lifting or thrust-generating body and/or the airfoil has reduced drag and noise when traveling through a fluid. 
     
     
         189 . The apparatus of  claim 181 , wherein at least a portion of the lifting and/or thrust-generating body and/or the airfoil has a chord length that varies continuously in an oscillatory fashion. 
     
     
         190 . The apparatus of  claim 189 , wherein the chord length variation is periodic. 
     
     
         191 . The apparatus of  claim 189 , wherein the one or more structures are printed and/or stamped from a sheet material that can be applied to the lifting and/or thrust-generating body and/or the airfoil. 
     
     
         192 . The apparatus of  claim 191 , wherein the one or more structures comprise one or more features directly molded into a surface of the one or more structures. 
     
     
         193 . The apparatus of  claim 192 , wherein the lifting and/or thrust-generating body and/or the airfoil comprises a windmill blade. 
     
     
         194 . The apparatus of  claim 189 , wherein the one or more structures are configured to be combined with an additional structure selected from the group consisting of: a compliant structure, a riblet, a compound riblet, a three-dimensional riblet, a shaped riblet, and combinations thereof. 
     
     
         195 . The method of  claim 185 , wherein at least a portion of the lifting and/or thrust-generating body and/or the airfoil has a chord length that varies continuously in an oscillatory fashion. 
     
     
         196 . The method of  claim 195 , wherein the chord length variation is periodic. 
     
     
         197 . The method of  claim 195 , wherein the one or more structures are printed and/or stamped from a sheet material that can be applied to the lifting and/or thrust-generating body and/or the airfoil. 
     
     
         198 . The method of  claim 197 , wherein the one or more structures comprise one or more features directly molded into a surface of the one or more structures. 
     
     
         199 . The method of  claim 198 , wherein the lifting and/or thrust-generating body and/or the airfoil comprises a windmill blade. 
     
     
         200 . The method of  claim 195 , wherein the one or more structures are configured to be combined with an additional structure selected from the group consisting of: a compliant structure, a riblet, a compound riblet, a three-dimensional riblet, a shaped riblet, and combinations thereof. 
     
     
         201 . The method of  claim 1 , wherein the at least one three-dimensional contour shaped surface reduces wake vortex structures at a tip region of the one or more lifting and/or thrust-generating bodies, and/or other surfaces, thereby promoting chord-wise air flow. 
     
     
         202 . The method of  claim 42 , wherein the at least one contour-shaped surface reduces wake vortex structures at a tip region of the one or more lifting and/or thrust-generating bodies, and/or other surfaces, thereby promoting chord-wise air flow. 
     
     
         203 . The method of  claim 58 , wherein the one or more contour shapes reduce wake vortex structures at a tip region of the one or more lifting and/or thrust-generating surface, thereby promoting chord-wise air flow. 
     
     
         204 . The apparatus of  claim 64 , wherein the surface enables reduction of wake vortex structures at a tip region of the surface, thereby promoting chord-wise air flow. 
     
     
         205 . The method of  claim 123 , wherein the one or more variations in geometric structure reduces wake vortex structures at a tip region of the one or more propeller blades, thereby promoting chord-wise air flow. 
     
     
         206 . The method of  claim 134 , wherein the one or more oscillating geometric shapes reduces wake vortex structures at a tip region of the surface, thereby promoting chord-wise air flow. 
     
     
         207 . The method of  claim 145 , wherein the surface enables reduction of wake vortex structures at a tip region of the surface, thereby promoting chord-wise air flow. 
     
     
         208 . The apparatus of  claim 177 , wherein the at least one three-dimensional contour-shaped surface reduces wake vortex structures at a tip region of the one or more lifting and/or thrust-generating bodies, thereby promoting chord-wise air flow. 
     
     
         209 . The apparatus of  claim 178 , wherein the at least one contour-shaped surface reduces wake vortex structures at a tip region of the one or more lifting and/or thrust-generating bodies, and/or other surfaces, thereby promoting chord-wise air flow. 
     
     
         210 . The apparatus of  claim 179 , wherein the one or more contour shapes reduces wake vortex structures at a tip region of the surface, thereby promoting chord-wise air flow. 
     
     
         211 . The apparatus of  claim 180 , wherein the surface enables reduction of wake vortex structures at a tip region of the surface, thereby promoting chord-wise air flow. 
     
     
         212 . An aerodynamic or hydrodynamic surface comprising:
 a plurality of geometric features; and   a plurality of variations in shape, wherein at least one of the plurality of variations is located at a trailing edge and/or a leading edge of the surface.   
     
     
         213 . The aerodynamic or hydrodynamic surface of  claim 212 , wherein the plurality of geometric features is applied across the trailing edge of the surface. 
     
     
         214 . The aerodynamic or hydrodynamic surface of  claim 213 , wherein the plurality of geometric features is applied in a periodic manner and promotes chord-wise fluid flow. 
     
     
         215 . The aerodynamic or hydrodynamic surface of  claim 212 , wherein the plurality of variations has a size selected from the group consisting of: macroscopic, microscopic, nanoscopic, and combinations thereof. 
     
     
         216 . The aerodynamic or hydrodynamic surface of  claim 212 , wherein the plurality of geometric features is positioned on the aerodynamic or hydrodynamic surface to induce or promote turbulent chord-wise fluid flow over the surface, thereby promoting chaotic fluid mixing of a fluid boundary layer. 
     
     
         217 . The aerodynamic or hydrodynamic surface of  claim 212 , wherein the plurality of geometric features results in mixing of a lower fluid stream and an upper fluid stream passing over the aerodynamic or hydrodynamic surface such that a time and a position of the mixing is varied across the trailing edge of the aerodynamic or hydrodynamic surface. 
     
     
         218 . The aerodynamic or hydrodynamic surface of  claim 217 , wherein a size and a duration of trailing wake vortex structures generated from a tip region of the aerodynamic or hydrodynamic surface is reduced, thereby reducing drag and noise when the aerodynamic or hydrodynamic surface is traveling through a fluid. 
     
     
         219 . An apparatus comprising a surface, the surface comprising:
 one or more oscillatory variations in at least one dimension; and/or   one or more corrugated and/or serrated portions; and/or   a plurality of geometrically-shaped projections extending along a spanwise direction of the surface.   
     
     
         220 . An apparatus for providing increased control and/or reduced noise of a surface, the apparatus comprising:
 one or more oscillating geometric shapes along at least a portion of the surface, wherein the surface comprises a leading edge and/or a trailing edge.   
     
     
         221 . The apparatus of  claim 220 , wherein the surface is an aerodynamic or hydrodynamic surface. 
     
     
         222 . The apparatus of  claim 221 , wherein the apparatus is selected from the group consisting of: windmill blades, fan blades, propeller blades, aircraft wings, aircraft control surfaces, helicopter rotor blades, and combinations thereof. 
     
     
         223 . The apparatus of  claim 220 , wherein the one or more oscillating geometric shapes provide passive boundary layer control of the leading edge. 
     
     
         224 . The apparatus of  claim 220 , wherein the one or more oscillating geometric shapes generate a plurality of wake vortices along a span of the leading edge that have a lower kinetic energy than concentrated wake vortex structures generated in the absence of the one or more oscillating geometric shapes. 
     
     
         225 . The apparatus of  claim 224 , wherein the one or more oscillating geometric shapes reduce airflow separation due to the plurality of wake vortices permitting airflow to remain attached to the surface. 
     
     
         226 . The apparatus of  claim 220 , wherein the one or more oscillating geometric shapes generate a plurality of wake vortices past the trailing edge that are smaller in intensity than wake vortices generated in the absence of the one or more oscillating geometric shapes. 
     
     
         227 . The apparatus of  claim 220 , wherein the one or more oscillating geometric shapes comprise one or more serrations and/or saw-toothed serrations. 
     
     
         228 . The apparatus of  claim 227 , wherein the one or more serrations and/or saw-toothed serrations are shaped like an owl feather. 
     
     
         229 . The apparatus of  claim 227 , wherein the one or more serrations and/or saw-toothed serrations are shaped like denticles. 
     
     
         230 . The apparatus of  claim 179 , wherein the surface comprises a lifting and/or thrust-generating surface. 
     
     
         231 . An apparatus comprising a surface, the surface comprising:
 one or more geometric variations in length in a chordwise direction along a span-wise direction of the surface; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular portions; and/or   one or more corrugated, serrated, convoluted, geometrically regular, and/or geometrically irregular edges.   
     
     
         232 . The method of  claim 195 , wherein the varying chord length promotes chord-wise fluid flow.