Method to control flow separation over an airfoil

1. A method to control flow separation over an airfoil, comprising:

providing an airfoil, having:

a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge, the upper surface being contoured from the leading edge to the trailing edge, the lower surface being positioned below the upper surface;

providing a flow separation control device, having:

a plurality of openings extending through a skin on the upper surface of the body;

a plurality of capillary tubes in gaseous communication with the plurality of openings;

a common reservoir positioned within the body and in gaseous communication with the plurality of capillary tubes, the plurality of capillary tubes extending from the plurality of openings and into the reservoir;

an inlet tube extending from the lower surface of the body and into the common reservoir;

a sensor to detect flow separation above the upper surface; and

a control system in communication with the sensor, a pump, and a flow regulator;

injecting gas, via the pump, from below the airfoil such that the gas enters the inlet tube first, travels to the common reservoir, and then travels through the plurality of capillary tubes into a portion of the airstream passing over the upper surface of the body; and

altering a flow rate of the injected gas above the upper surface via the control system and flow regulator based on data received from the sensor, wherein the flow rate is increased or decreased based on the data;

wherein the injected gas reduces a flow separation in the portion of the airstream passing over the upper surface of the body.

2. The method of claim 1 , wherein the airfoil is a wing of an aircraft.

3. The method of claim 2 , further comprising:

extending the flow separation device along the longitudinal length of the wing.

4. The method of claim 3 , further comprising:

a porous section created by the plurality of openings of the flow separation control device extending from a ⅓ chord length to a ⅔ chord length of the airfoil.

5. The method of claim 1 , wherein the plurality of openings having a circular shaped dimension.

6. The method of claim 1 , further comprising:

a porous section created by the plurality of openings of the flow separation control device extending from a ⅓ chord length to a ⅔ chord length of the airfoil.

7. The method of claim 1 , further comprising:

orienting the plurality of capillary tubes at an angle relative to the upper surface of the body.

8. The method of claim 7 , further comprising:

injecting the gas at an angle relative to the upper surface of the body.