Plate member for reducing drag on a fairing of an aircraft
A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.
1. A rotary wing aircraft comprising:
a fuselage including a plurality of surfaces;
at least one engine mounted in the fuselage;
a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft, the rotor assembly including a plurality of surface portions;
a rotor shaft fairing extending between the fuselage and the rotor assembly and about at least a portion of the rotor shaft, the rotor shaft fairing including a first surface facing the fuselage, a second, opposing surface facing away from the fuselage and an intermediate portion defined, at least in part by the leading edge portion, trailing edge portion and first and second side portions; and
a plate member mounted to one of the first surface and the second surface and projecting proudly of at least a portion of the rotor shaft fairing, the plate member increasing an aspect ratio of and reducing induced drag on the rotor shaft fairing.
2. The rotary wing aircraft according to claim 1 , wherein the rotor shaft fairing includes a leading edge surface portion, a trailing edge surface portion, a first lateral side surface portion extending between the leading edge surface portion and the trailing edge surface portion and a second, opposing lateral side surface portion extending between the leading edge portion and the trailing edge portion, the plate member projecting proudly of the trailing edge portion and at least a portion of each of the first and second lateral side portions.
3. The rotary wing aircraft according to claim 1 , wherein the plate member includes a first plate member mounted to the first surface and a second plate member mounted to the intermediate portion.
4. The rotary wing aircraft according to claim 1 , wherein the plate member includes a first plate member mounted to the second surface and a second plate member mounted to the intermediate portion.
5. The rotary wing aircraft according to claim 1 , wherein the plate member includes a first plate member mounted to the first surface and a second plate member mounted to the intermediate portion, and a third plate member mounted to the second surface.
6. The rotary wing aircraft according to claim 1 , wherein the plate member includes a first plate member mounted to the first surface and a second plate member mounted to the second surface.
7. The rotary wing aircraft according to claim 1 , wherein the rotor shaft fairing includes a chord length, the plate member projecting proudly of the rotor shaft fairing between about 2% and about 17% of the chord length.
8. The rotary wing aircraft according to claim 7 , wherein the plate member projects proudly of the rotor shaft fairing between about 8% and about 13% of the chord length.
9. The rotary wing aircraft according to claim 8 , wherein the rotor shaft fairing includes a first surface facing the fuselage, a second, opposing surface facing away from the fuselage and an intermediate portion defined, at least in part, by the outer surface extending therebetween, the plate member being mounted to one of the first surface and the second surface.
10. The rotary wing aircraft according to claim 9 , wherein the plate member includes a first plate member mounted to the first surface and a second plate member mounted to the second surface.
11. The rotary wing aircraft according to claim 10 , wherein the active air discharge opening extends between the first and second plate members.
12. The rotary wing aircraft according to claim 1 , further comprising:
an active air discharge opening extending through the outer surface of the rotor shaft fairing; and
an active air generation system mounted in one of the fuselage and the rotor assembly, the active air generation system being configured and disposed to generate and direct a flow of air out through the active air discharge opening to disrupt an airstream flowing over the outer surface of the rotor shaft fairing.