Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft
View Patent ↗An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.
1. A vertical take-off and vertical landing rotor aircraft comprising:
a surface over which a turbulent vortex generating airflow passes when in use, the turbulent flow being generated by a movement of the surface and a velocity of the airflow relative to the surface is greater than about 10 m/s, and
a plasma actuator configured to generate a plasma above the surface of the vertical take-off and vertical landing rotor aircraft, the plasma coupling a directed momentum into the air surrounding the surface of the vertical take-off and vertical landing rotor aircraft to reduce separation of the airflow from the surface of the vertical take-off and vertical landing rotor aircraft,
wherein the plasma actuator comprises:
a dielectric,
a first electrode on a first side of the dielectric, the first electrode having a first surface in contact with the dielectric and a second surface opposite the first surface exposed to the surrounding air,
a second electrode covered by a second side of the dielectric, and
an alternating current voltage source connected between the first and second electrodes, and
wherein an amount of separation of the turbulent vortex generating airflow from the surface of the vertical take-off and vertical landing rotor aircraft depends on a velocity of the airflow and a frequency of the alternating current voltage source, wherein based upon the velocity of airflow, a frequency of the alternating current voltage source is selected so as to reduce the amount of separation of the airflow from the surface of the vertical take-off and vertical landing rotor aircraft.
2. The aircraft according to claim 1 , wherein the dielectric is polyimide tape.
3. The aircraft according to claim 1 , wherein the dielectric is ceramic.
4. The aircraft according to claim 1 , wherein each of the first and second electrodes is a copper foil.
5. The aircraft according to claim 1 , wherein edges of the first and second electrodes overlap.
6. The aircraft according to claim 1 , wherein the surface is provided on an airfoil.
7. The aircraft according to claim 6 , wherein the aircraft is a tilt-rotor aircraft and the airfoil is a wing.
8. The aircraft according to claim 7 , wherein the wing includes a first section and a second section, the second section being pivotable with respect to the first section, and the plasma actuator is provided on the second section.
9. The aircraft according to claim 6 , wherein the aircraft is a helicopter and the airfoil is a rotor.
10. The aircraft according to claim 6 , wherein the plasma actuator is configured to generate a plasma over essentially an entire spanwise dimension of the airfoil.
11. The aircraft according to claim 6 , wherein the plasma actuator is provided on a leading edge of the airfoil.
12. The aircraft according to claim 1 , wherein the surface is provided on a fuselage of the aircraft.
13. The aircraft according to claim 1 , wherein the surface is provided on a nacelle of the aircraft.
14. The aircraft according to claim 1 , wherein the alternating current voltage source is configured to apply voltage between the first and second electrodes at a steady frequency.
15. The aircraft according to claim 1 , wherein the alternating current voltage source is configured to apply a voltage between the first and second electrodes at an unsteady frequency.
16. The aircraft according to claim 1 , wherein the alternating current voltage source is configured to selectively apply a voltage between the first and second electrodes at a steady frequency or an unsteady frequency.
17. The aircraft according to claim 1 , wherein a plurality of plasma actuators are provided on the surface.
18. The aircraft according to claim 1 , wherein the frequency is selected such that a Strouhal number depending upon the frequency and the velocity of the airflow is approximately unity.
19. A method of reducing separation of a turbulent vortex generating airflow from a surface of a vertical take-off and vertical landing rotor aircraft, the comprising:
applying an alternating current voltage between a first and a second electrodes at a steady frequency or an unsteady frequency, the first electrode having a first surface in contact with a first side of a dielectric and a second surface opposite the first surface exposed to surrounding air, the second electrode having a surface in contact with a second side of the dielectric;
generating a plasma in air surrounding the surface of the vertical take-off and vertical landing rotor aircraft at a position where the airflow would separate from the surface of the vertical take-off and vertical landing rotor aircraft in the absence of the plasma, a velocity of the airflow relative to the surface is greater than about 10 m/s; and
selecting a frequency of the alternating current voltage source based upon a velocity of the turbulent vortex generating airflow passing over the surface of the vertical take-off and vertical landing rotor aircraft so as to reduce an amount of separation of the airflow from the surface of the vertical take-off and vertical landing rotor aircraft.
20. A method according to claim 19 , further comprising:
oscillating the surface; and
applying an alternating current voltage between the first and second electrodes at a steady frequency or an unsteady frequency.
21. A method according to claim 20 , wherein applying the alternating current voltage comprises applying the alternating current voltage selectively during the oscillation of the surface.
22. A method according to claim 19 , wherein the frequency is selected such that a Strouhal number depending upon the frequency and the velocity of the airflow is approximately unity.
23. A vertical take-off and vertical landing rotor aircraft comprising:
a surface over which a turbulent vortex generating airflow passes when in use, the turbulent flow being generated by a movement of the surface and a velocity of the airflow relative to the surface is greater than about 10 m/s, and
a plasma actuator configured to generate a plasma above the surface of the vertical take-off and vertical landing rotor aircraft, the plasma coupling a directed momentum into the air surrounding the surface of the vertical take-off and vertical landing rotor aircraft to reduce separation of the airflow from the surface of the vertical take-off and vertical landing rotor aircraft,
wherein the plasma actuator comprises:
a dielectric,
a first electrode on a first side of the dielectric, the first electrode having a first surface in contact with the dielectric and a second surface opposite the first surface exposed to the surrounding air,
a second electrode covered by a second side of the dielectric, and
an alternating current voltage source connected between the first and second electrodes, and
wherein an amount of separation of the turbulent vortex generating airflow from the surface of the vertical take-off and vertical landing rotor aircraft depends on a velocity of the airflow and a frequency of the alternating current voltage source, and based upon the velocity of the airflow, a frequency of the alternating current voltage source is selected so as to reduce the amount of separation of the airflow from the surface of the vertical take-off and vertical landing rotor aircraft.