FIELD: aviation.
SUBSTANCE: invention relates in particular to the structures of rotary-wing aircraft. The rotorcraft with a fuselage has a centerline 230, at least one main rotor that generates vortices during operation, and a stabilizer wing 200. The stabilizer wing 200 is shaped in plan that reduces unstable aerodynamic loads caused by the wake stream of at least one main rotor. In particular, the stabilizer wing 200 may be provided with a left wing end 260, a right wing end 260, a quarter-chord line 240 with non-zero curvature so that the interaction between the vortices generated by at least one rotor and the quarter-chord line 240 is timed, a leading edge 210 that is arcuate, and a trailing edge 220 that is arcuate.
EFFECT: improvement of controllability and flight stability is provided.
16 cl, 10 dwg, 3 tbl
| Title | Year | Author | Number |
|---|---|---|---|
| ROTARY-WING UNMANNED AERIAL VEHICLE OF TANDEM SCHEME | 2021 |
|
RU2771195C1 |
| UNMANNED HIGH-SPEED HELICOPTER-AIRPLANE | 2017 |
|
RU2664024C2 |
| PROPELLER BLADE, PROPELLER, AIRCRAFT AND METHOD | 2013 |
|
RU2524757C1 |
| HYBRID AIRCRAFT WITH ROTARY BEARING SURFACE | 2012 |
|
RU2522373C2 |
| ROTORCRAFT | 2019 |
|
RU2720746C1 |
| HIGH-SPEED TURBOFAN COMBINED HELICOPTER | 2016 |
|
RU2629475C1 |
| ROTARY-WING AIRCRAFT | 2017 |
|
RU2673754C2 |
| HEAVY HIGH-SPEED ROTARY-WING AIRCRAFT | 2016 |
|
RU2608122C1 |
| FAST-SPEED CONVERTIBLE COMPOUND HELICOPTER | 2015 |
|
RU2609856C1 |
| HYBRID AIRCRAFT | 1996 |
|
RU2160689C2 |
