Airfoil shaped tail boom

1. A rotary aircraft, comprising:

a fuselage;

an engine carried by the fuselage;

a rotor rotatably attached to the engine; and

a tail boom rotatably attached to and extending from the fuselage, the tail boom being configured to rotate about a longitudinal axis relative to the fuselage during flight to manipulate rotorwash, the tail boom having:

a body having:

a first side surface and an opposing second side surface, the first side surface contoured to act as a pressure surface of an airfoil and the second side surface contoured to act as a suction surface of an airfoil; and

a leading and an opposing trailing edge, extending; and

a flap pivotally attached to the trailing edge of the tail boom;

wherein the engine rotates the rotor, thereby creating downward rotorwash and thereby exerting a torque on the fuselage;

wherein the rotorwash flows around the first side surface and the second side surface of the tail boom, resulting in a high-pressure region forming near the first side surface and resulting in a low-pressure region forming near the second side surface;

wherein the pressure difference between the high-pressure region and the low- pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage;

wherein the flap is configured to further control the flow of rotorwash with a surface contouring, thereby manipulating the directional movement of the rotorwash flowing around the tail boom;

an anti-torque system attached to the tail boom; and

wherein the anti-torque system is a tail rotor.

2. The rotary aircraft according to claim 1 , wherein the rotary aircraft is a helicopter.

3. The rotary aircraft according to claim 1 , further comprising:

a flow control device attached to the body of the tail boom.

4. The rotary aircraft according to claim 1 , wherein the angle of attack of the tail boom with respect to the rotorwash is approximately six degrees.

5. A rotary aircraft, comprising:

a fuselage;

an engine carried by the fuselage;

a rotor rotatably attached to the engine;

a tail boom rotatably attached to and extending from the fuselage, the tail boom being configured to rotate about a longitudinal axis relative to the fuselage during flight to manipulate rotorwash, the tail boom having:

a body having a first side surface and an opposing second side surface, the first side surface contoured to act as a pressure surface of an airfoil and the second side surface contoured to act as a suction surface of an airfoil;

a leading and an opposing trailing edge;

a flap pivotally attached to the trailing edge; and

an anti-torque system attached to the tail boom;

wherein the engine rotates the rotor, thereby creating downward rotorwash and exerting a torque on the fuselage;

wherein the rotorwash flows around the first side surface and the second side surface of the tail boom, resulting in a high-pressure region forming near the first side surface and resulting in a low-pressure region forming near the second side surface;

wherein the anti-torque system and the tail boom create a resultant lateral force in a direction opposing the torque on the fuselage;

wherein the flap is configured to further control the flow of rotorwash with a surface contouring, thereby manipulating the directional movement of the rotorwash flowing around the tail boom; and

wherein the anti-torque system is a tail rotor.

6. The rotary aircraft according to claim 5 , wherein the rotary aircraft is a helicopter.

7. The rotary aircraft according to claim 5 , further comprising:

a flow control device attached to the body of the tail boom.

8. The rotary aircraft according to claim 5 , wherein the angle of attack of the tail boom with respect to the rotorwash is approximately six degrees.

9. A method for controlling a fuselage torque created by an engine carried by the fuselage of a rotary aircraft, the method comprising:

creating a lateral force in a direction opposing the fuselage torque with a tail boom, the tail boom having:

a body having a first side surface and an opposing second side surface, the first side surface contoured to act as a pressure surface of an airfoil and the second side surface contoured to act as a suction surface of an airfoil;

positioning the tail boom within rotorwash created by the rotary aircraft such that the rotorwash passing over the first side surface forms a high-pressure region near the first side surface and wherein the rotorwash passing over the second side surface forms a low-pressure region near the second side surface;

creating a lateral force with a flap pivotally attached to the tail boom; and

creating a lateral force by rotating the tailboom about a longitudinal axis relative to the fuselage;

wherein the lateral force opposes the fuselage torque;

wherein the pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move in a direction towards the low-pressure region, resulting in a lateral force opposing the fuselage torque;

wherein the flap is configured to control the flow of rotorwash with a surface contouring, thereby manipulating the directional movement of the rotorwash flowing around the tail boom.

creating a lateral force with an anti-torque system attached to the body of the tail boom;

wherein the anti-torque system is a tail rotor; and

wherein the lateral force opposes the fuselage torque.