Spin resistant aircraft configuration
A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.
1. A configuration for an aircraft so as to be spin resistant, said aircraft comprising a fuselage including a T-tail configuration and a high wing having a leading edge coupled to an upper portion of the fuselage wherein the high wing includes a first region adjacent to the fuselage and a second region adjacent to a wing tip, the first region being contiguous with the second region, wherein the first region includes an effective first wing twist and the second region includes an effective second wing twist and wherein the effective first wing twist is at or between 0.5-3.0 degrees and the effective second wing twist is at or between 0.5-3.0 degrees, and wherein the wing includes a discontinuity in the leading edge to constrain, at high angles of attack, a stall cell and associated separated airflow to remain within the first region and flow so as to remain apart from flight controls located within the second region and flight controls associated with the T-tail.
2. The configuration for an aircraft as defined in claim 1 , wherein the leading-edge discontinuity includes a cuff positioned at 50% semi-span operable to form an aerodynamic boundary between the first region and the second region.
3. The configuration for an, aircraft as defined in claim 2 , wherein the cuff includes a delta vortex generator.
4. The configuration for an aircraft as defined in claim 1 , wherein the, first region includes one or more stall strips associated with a leading edge of the wing.
5. The configuration for an aircraft as defined in claim 4 , wherein at least one of the one or more stall strips is coupled to the leading edge of the wing and angled downward as it extends toward the wing tip.
6. The configuration for an aircraft as defined in claim 5 , wherein at least one of the one or more stalls strips is coupled to and parallel with the leading edge of the wing.
7. The configuration for an aircraft as defined in claim 1 , wherein the second region includes vortex generators.
8. The configuration for an aircraft as defined in claim 1 , wherein the combined wing twist is such that a wing tip angle of incidence is less than a wing root angle of incidence.
9. The configuration for an aircraft as defined in claim 8 , wherein the wing twist of the first region is substantially different than the wing twist of the second region.
10. The configuration for an aircraft as defined in claim 1 , wherein the wing tip is swept forward.
11. The configuration for an aircraft as defined in clam 1 , wherein the T-tail includes swept tips.
12. A system for a spin resistant configuration in an aircraft, the system comprising:
a fuselage having a T-tail wherein the T-tail includes a span and wherein the span of the T-tail is optimized to maintain controllability during a stall;
a wing associated with the an upper portion of the fuselage having a wing root and a wing tip and wherein the wing includes a first region near the wing root and a second region near the wing tip and wherein the first region and the second region are contiguous along a contiguous border wherein the first region includes an effective first wing twist and the second region includes an effective second wing twist and wherein the effective first wing twist is at or between 0.5-3.0 degrees and the effective second wing twist is at or between 0.5-3.0 degrees; and
a leading edge discontinuity operable at high angles of attack to form an aerodynamic fence along the contiguous border isolating a stall cell and associated separated airflow to remain within the first region and flow apart from any control surfaces in the second region of the wing and those associated with the T-tail.
13. The system for a spin resistant configuration in an aircraft according to claim 12 , wherein responsive to a stall cell being developed within the first region, control surfaces of the aircraft remain operational to control the aircraft.
14. The system for a spin resistant configuration in an, aircraft according to claim 13 , wherein aircraft control surfaces are isolated from the stall cell.
15. The system for a spin resistant configuration, in an aircraft according to claim 12 , further comprising a plurality of vortex generators associated with the second region.
16. The system for a spin resistant configuration in an aircraft according to claim 12 , further comprising one or more stall strips associated with a leading edge of the wing in the first region.
17. The system for a spin resistant configuration in an aircraft according to claim 16 , wherein one of the one or more stalls strips is coupled to the leading edge of the wing and angled downward as it extends toward the wingtip.
18. The system for a spin resistant configuration in an aircraft according to claim 16 , wherein one of the one or more stall strips is coupled to and parallel with the leading edge of the wing.
19. The system for a spin resistant configuration in an aircraft according to claim 12 , wherein a combined wing twist is such that a wing tip angle of incidence is less than a wing root angle of incidence.
20. The system for a spin resistant configuration in an aircraft according to claim 19 , wherein the wing twist of the first region is substantially different than the wing twist of the second region.