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An apparatus may comprise a first skin panel having a first surface, a second skin panel having a second surface, a first flange located at an end of the first skin panel, a second flange located at an end of the second skin panel, and a strip having a third surface. The first skin panel may be loca

An apparatus may comprise a first skin panel having a first surface, a second skin panel having a second surface, a first flange located at an end of the first skin panel, a second flange located at an end of the second skin panel, and a strip having a third surface. The first skin panel may be located adjacent to the second skin panel such that the first flange and the second flange form a channel. The strip may be bonded in the channel. Fluid flow over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel may have a desired state.

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1. An apparatus for directing fluid flow over a set of surfaces, comprising: a first skin panel having a first surface;a second skin panel having a second surface;a first flange located at an end of the first skin panel;a second flange located at an end of the second skin panel, in which the first s

1. An apparatus for directing fluid flow over a set of surfaces, comprising: a first skin panel having a first surface;a second skin panel having a second surface;a first flange located at an end of the first skin panel;a second flange located at an end of the second skin panel, in which the first skin panel is located adjacent to the second skin panel such that the first flange and the second flange form a channel; anda strip having a third surface, in which the strip is bonded in the channel to the first flange and to the second flange, in which fluid flow over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel has a desired state, the strip substantially occupying the channel such that fluid flow passes substantially over the first surface of the first skin, the second surface of the second skin, and the third surface of the strip and is restricted from flowing under the first skin, the second skin, and the strip. 2. The apparatus of claim 1, wherein the desired state of the fluid flow at a boundary layer is a substantially laminar airflow. 3. The apparatus of claim 1 further comprising: a plurality of fasteners, wherein the plurality of fasteners attach the first flange and the second flange to a support structure. 4. The apparatus of claim 3, wherein the support structure is selected from one of a spar, a frame, a stringer, a clip, and a rib. 5. The apparatus of claim 1, wherein a first gap is present between a first side of the strip and the end of the first skin panel and a second gap is present between a second side of the strip and the end of the second skin panel. 6. The apparatus of claim 1 further comprising: a coating attached to at least a portion of the first surface of the first skin panel, wherein the coating extends into the channel. 7. The apparatus of claim 1 further comprising: an aircraft, wherein the first skin panel and the second skin panel are located on the aircraft. 8. The apparatus of claim 1, wherein the first skin panel and the second skin panel are comprised of a material selected from one of aluminum, steel, titanium, and a composite material. 9. The apparatus of claim 1, wherein the strip is comprised of a material selected from one of aluminum, steel, titanium, and a composite material. 10. The apparatus of claim 1 further comprising: an adhesive, wherein the adhesive bonds in the channel and the adhesive is configured to act as a sealant. 11. The apparatus of claim 3, wherein the plurality of fasteners have a plurality of heads and wherein the plurality of heads is substantially coplanar to a surface of the first flange and a surface of the second flange through which the plurality of fasteners extend. 12. The apparatus of claim 11, wherein the plurality of heads has a non-stick coating. 13. The apparatus of claim 1, wherein the first skin panel, the second skin panel, the first flange, the second flange, and the strip form a joint, and wherein the joint is located on a platform. 14. The apparatus of claim 13, wherein the platform is selected from one of a mobile platform, a stationary platform, an aircraft, a submarine, a bus, a personnel carrier, a tank, a train, an automobile, a spacecraft, and a surface ship. 15. An aircraft joint comprising: a first skin panel having a first surface, in which the first skin panel is located on an aircraft;a second skin panel having a second surface, in which the second skin panel is located on the aircraft, and in which the first skin panel and the second skin panel are comprised of a material selected from one of aluminum, steel, titanium, and a composite material;a first flange located at an end of the first skin panel;a second flange located at an end of the second skin panel, in which the first skin panel is located adjacent to the second skin panel such that the first flange and the second flange form a channel;a plurality of fasteners, in which the plurality of fasteners attach the first flange and the second flange to a spar, in which the plurality of fasteners has a plurality of heads having a non-stick coating, and in which the plurality of heads is substantially coplanar to a surface of the first flange and a surface of the second flange through which the plurality of fasteners extend;a strip having a third surface, in which the strip is bonded in the channel, in which a first gap is present between a first side of the strip and the end of the first skin panel and a second gap is present between a second side of the strip and the end of the second skin panel, and in which the strip is comprised of a material selected from one of aluminum, steel, titanium, and the composite material;an adhesive, in which the adhesive bonds the strip in the channel, and in which the adhesive is configured to act as a sealant; anda coating attached to at least a portion of the first surface of the first skin panel, in which the coating extends into the channel, such that airflow is directed over the third surface of the strip, the first surface of the first skin panel, and the second surface of the second skin panel and such that the airflow has a substantially laminar airflow. 16. An apparatus for directing airflow over a wing, comprising: a first skin panel having an upper surface, the first skin panel proximate a leading edge of the aircraft, the first skin panel comprising one of aluminum, steel, and titanium;a second skin panel having an upper surface, the second skin panel comprising a composite material;a first flange located at an end of the first skin panel, the first skin panel attached to the first flange;a second flange located at an end of the second skin panel, the second skin panel formed with the second flange, in which the first skin panel is located adjacent to the second skin panel such that the first flange and the second flange form a channel; anda single material strip having an upper surface, in which the strip is bonded in the channel to the first flange and to the second flange so as to substantially occupy the channel such that air flows over the upper surface of the first skin, the upper surface of the second skin, and the upper surface of the strip, and such that air flows in a desired state. 17. The apparatus of claim 16, wherein the strip substantially contacts the first flange and the second flange so as to prevent air flow between the strip and the first flange and the second flange. 18. The apparatus of claim 16, wherein the first skin panel and the second skin panel do not substantially move with respect to the strip. 19. The apparatus of claim 16, wherein the strip is bonded in the channel with adhesive so as to restrict airflow to the upper surface of the strip. 20. The apparatus of claim 16, wherein the upper surface of the first skin panel, the upper surface of the second skin panel, and the supper surface of the strip substantially align along a common plane. 21. The apparatus of claim 1, wherein the first skin panel is attached to the first flange and the second skin panel is formed with the second flange. 22. The apparatus of claim 21 wherein the first skin panel comprises a metal skin and the second skin panel comprises a composite skin. 23. The apparatus of claim 22, wherein the first skin panel comprises titanium. 24. The apparatus of claim 1, wherein the first skin panel and the first flange comprise separate structures.