Main rotor blade and helicopter
A main rotor blade 1 , which is the main rotor blade 1 for a high-velocity helicopter, includes: a blade root part 10 having a length of 30% or more of a rotor radius R; and a blade main body 20 continuous with the blade root part 10 . Preferably, a cross-sectional shape of the blade root part 10 satisfies (x/a) m +(y/b) m =1 and a>b, where m: arbitrary number, x: chord length direction, and y: blade thickness direction.
1. A main rotor blade, comprising:
a blade root part having a length of 30% or more of a rotor radius; and
a blade main body continuous with the blade root part,
wherein a chord length of the blade main body has a maximum value at a position in a range of 50% to 90% of the rotor radius, and the maximum value is 1.6 times to 1.8 times as long as a reference chord length of an interface part between the blade root part and the blade main body.
2. The main rotor blade according to claim 1 ,
wherein a cross-sectional shape of the blade root part satisfies (x/a) m +(y/b) m =1 and a>b where
m: arbitrary number,
x: chord length direction, and
y: blade thickness direction.
3. The main rotor blade according to claim 1 , wherein
a torsion angle of the blade main body has a minimum value at a position in a range of 80% to 95% of the rotor radius, and is reduced from a blade root side and from a blade tip side to the position.
4. The main rotor blade according to claim 1 , wherein
a blade tip of the blade main body has a hedral angle of −30° to 30°.
5. The main rotor blade according to claim 1 , wherein a chord length of a blade tip of the blade main body is 30% or less of the reference chord length of the interface part between the blade root part and the blade main body.
6. The main rotor blade according to claim 1 , wherein
a blade tip of the blade main body has a swept-back angle of 60° or less.
7. A helicopter, comprising:
a main rotor blade including
a blade root part having a length of 30% or more of a rotor radius, and
a blade main body continuous with the blade root part,
wherein a chord length of the blade main body of the main rotor blade has a maximum value at a position in a range of 50% to 90% of the rotor radius, and the maximum value is 1.6 times to 1.8 times as long as a reference chord length of an interface part between the blade root part and the blade main body.
8. The helicopter according to claim 7 ,
wherein a cross-sectional shape of the blade root part of the main rotor blade satisfies (x/a) m +(y/b) m =1 and a>b
where
m: arbitrary number,
x: chord length direction, and
y: blade thickness direction.
9. The helicopter according to claim 7 , wherein
a torsion angle of the blade main body of the main rotor blade has a minimum value at a position in a range of 80% to 95% of the rotor radius, and is reduced from a blade root side and from a blade tip side to the position.
10. The helicopter according to claim 7 , wherein
a blade tip of the blade main body of the main rotor blade has a hedral angle of −30° to 30°.
11. The helicopter according to claim 7 , wherein a chord length of a blade tip of the blade main body of the main rotor blade is 30% or less of the reference chord length of the interface part between the blade root part and the blade main body.
12. The helicopter according to claim 7 , wherein
a blade tip of the blade main body of the main rotor blade has a swept-back angle of 60° or less.