An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling
An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.
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1. An air vehicle comprising: an airfoil designed for transonic flight, the airfoil having a region of supersonic flow during transonic flight, a surface of the airfoil having upstream and downstream orifices at or within the region; andan active flow control system for controlling air vehicle motio
1. An air vehicle comprising: an airfoil designed for transonic flight, the airfoil having a region of supersonic flow during transonic flight, a surface of the airfoil having upstream and downstream orifices at or within the region; andan active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region, the system creating an aerodynamic imbalance to move the shock wave. 2. The air vehicle of claim 1, wherein the active flow control system creates the aerodynamic imbalance through virtual changes to a local surface slope of a supersonic flow pocket, thereby moving the shock wave forward or aft. 3. The air vehicle of claim 1, wherein the upstream and downstream orifices are located at beginning and end of the region. 4. The air vehicle of claim 1, wherein the upstream orifice is at 50-65% of chord length of the airfoil and the downstream orifice is at 65-90% of chord length of the airfoil. 5. The air vehicle of claim 1, wherein each orifice includes a one-way valve such that air can only move into the upstream orifice through its valve and only move out of the downstream orifice through its valve. 6. The air vehicle of claim 1, wherein the upstream and downstream orifices are in fluid communication; and wherein the system includes an actuator for causing pulsing air to flow into the upstream orifice and out of the downstream orifice during transonic flight to alter the strength and location of the shock wave. 7. The air vehicle of claim 6, wherein the actuator is selectively operated to vary a phase differential of air flowing into the upstream orifice and out of the downstream orifice. 8. The air vehicle of claim 6, wherein the actuator is operated at a frequency between about 150 Hz and 350 Hz. 9. The air vehicle as set forth in claim 6 wherein air is drawn toward the upstream orifice at 80-100 degrees with respect to the surface, and air is pushed away from downstream orifice at 80-100 degrees with respect to the surface. 10. The air vehicle of claim 9, wherein the drawing and pushing of air is out of phase. 11. An aircraft comprising: opposing first and second wings for transonic flight, each wing having an upper surface and a lower surface, the upper surface having a region of supersonic flow, the upper surface of each wing having an upstream orifice at a beginning of the region, and a downstream orifice at an end of the region, the upstream orifice in fluid communication with the downstream orifice; andan active flow control system for controlling flow of air into the upstream orifice and out of the downstream orifice of at least one of the wings during transonic flight to alter strength and location of a shock wave in the region, the strength and location of the shock wave altered to control motion of the aircraft during transonic flight. 12. The aircraft of claim 11, wherein air is drawn toward the upstream orifice at 80-100 degrees with respect to the surface, and air is pushed away from downstream orifice at 80-100 degrees with respect to the surface. 13. The aircraft of claim 11, wherein the drawing and pushing of air is performed out of phase. 14. The aircraft of claim 11, wherein the wings are fixed wings. 15. The aircraft of claim 11, wherein the system includes an actuator for causing pulsing air to flow into the upstream orifice and out of the downstream orifice of each wing during transonic flight and thereby alter the shock wave strength and location. 16. The aircraft of claim 15, wherein each actuator is operated at a frequency between about 150 Hz and 350 Hz. 17. A method of operating an air vehicle having a surface designed for transonic air flow, the method comprising: operating the air vehicle under transonic conditions, whereby a shock wave is present at a region of the surface; andcontrolling motion of the air vehicle during transonic flight, the motion control including drawing air into a first orifice at a beginning of the shock wave and pushing air out of a second orifice at an end of the shock wave such that strength and location of the shock wave is altered to create an aerodynamic imbalance. 18. The method of claim 17, wherein air is drawn into the upstream orifice at an angle of 80-100 degrees with respect to the surface, and air is pushed away from downstream orifice at an angle of 80-100 degrees with respect to the surface. 19. The method of claim 17, wherein the drawing and pushing of air is out of phase. 20. The method of claim 17, wherein controlling the motion includes forcing physical changes in at least one of lift, drag, side forces, and moments of the air vehicle.
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