CN112173075A - Aerodynamic profile of helicopter low-noise rotor blade - Google Patents
Aerodynamic profile of helicopter low-noise rotor blade Download PDFInfo
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- CN112173075A CN112173075A CN202011028590.0A CN202011028590A CN112173075A CN 112173075 A CN112173075 A CN 112173075A CN 202011028590 A CN202011028590 A CN 202011028590A CN 112173075 A CN112173075 A CN 112173075A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Wind Motors (AREA)
Abstract
The invention belongs to the technical field of aerodynamic design of helicopters, and discloses an aerodynamic shape of a low-noise rotor blade of a helicopter. The aerodynamic shape of the blade adopts multi-section airfoil configuration, a forward and backward sweeping blade tip configuration, blade tip tapering and negative torsion design, and the aerodynamic noise of the rotor wing can be effectively reduced. The blade and reference blade noise measurement test is carried out in an acoustic wind tunnel, and the result shows that the blade noise is superior to the reference blade in a typical inclined descending state, the maximum amplitude of rotor noise is 6 decibels, and the average noise reduction amplitude is close to 4 decibels.
Description
Technical Field
The invention belongs to the technical field of aerodynamic design of helicopters, and particularly relates to an aerodynamic shape of a low-noise rotor blade of a helicopter.
Background
The helicopter is a widely used aircraft, but the external noise is one of the inherent disadvantages, especially in densely populated areas, which causes the helicopter to generate serious noise pollution and influence on the surrounding environment and ground personnel, and the factor greatly limits the further use of the helicopter. The rotor is one of the most main sources of external noise of the helicopter, so that the design of a helicopter low-noise rotor scheme is one of the key directions for the technical research of the design of the helicopter rotor. The noise of the traditional helicopter model in China is generally higher, and the low-noise rotor aerodynamic layout of the helicopter is still subject to innovation and breakthrough.
Disclosure of Invention
The purpose of the invention is as follows: provides a low-noise rotor blade aerodynamic profile of a helicopter so as to meet the requirement of a 'quiet' helicopter.
The technical scheme of the invention is as follows:
a main wing section of the helicopter rotor blade comprises three blade sections, wherein the three blade sections respectively adopt wing profiles of the same wing profile family, and the relative thicknesses of the wing profiles are 12%, 9% and 7%.
Preferably, the airfoil profile of the first section of the blade section is a 12% airfoil profile with relative thickness, and the 12% airfoil profile position is from the initial position of the blade airfoil profile to the position of 0.65R-0.85R of the relative radius; the airfoil profile of the second blade section is a transition section of 12% airfoil profile and 9% airfoil profile; the 9% airfoil profile is arranged between the relative radiuses of 0.85R-0.92R; the airfoil profile of the third section blade section is a transition section of 9% airfoil profile and 7% airfoil profile, and the 7% airfoil profile is arranged between the relative radiuses of 0.95R and 1.0R.
Preferably, the 12% airfoil position is from the blade airfoil starting position to 0.78R of the relative radius; the 9% airfoil was disposed at a relative radius of 0.85R; the 7% airfoil is disposed at a relative radius of 1.0R.
Preferably, the first section of the blade has a chord length of C; the chord length of the 9 percent airfoil section is 1C-1.5C, and the chord length of the second section of blade section is in linear transition; the chord length of the 7 percent airfoil section is 1/3-1/2C, and the chord length of the third section of blade section is in linear transition.
Preferably, the first blade section is rectangular in shape; the second section of blade section is in a forward swept shape, and the forward swept angle is-4 degrees to-15 degrees; the third section of the blade section is in a sweepback shape, and the sweepback angle is 10-30 degrees.
Preferably, the forward sweep angle of the second blade section is-6 °; the sweepback angle of the third section of blade section is 12 degrees.
Preferably, the blades are designed by linear pneumatic negative torsion, and the pneumatic torsion rate is-10 degrees/R to-14 degrees/R.
Preferably, the aerodynamic twist rate of the blade is-11 °/R.
Preferably, the aerodynamic twist rate of the third section of the blade section is 0.
The invention has the beneficial effects that: the aerodynamic shape of the blade adopts multi-section airfoil configuration, a forward and backward sweeping blade tip configuration, blade tip tapering and negative torsion design, and the aerodynamic noise of the rotor wing can be effectively reduced. A noise measurement test of the blade and a reference blade is carried out in an acoustic wind tunnel, and the result shows that the blade noise is superior to that of the reference blade in a typical inclined descending state, the maximum amplitude of rotor noise reaches 6 decibels (A weight), and the average noise reduction amplitude is close to 4 decibels (A weight).
Drawings
Figure 1 is a chord length distribution of a low noise rotor blade according to the present invention;
FIG. 2 is a twist angle distribution for a low noise rotor blade according to the present invention;
figure 3 is a schematic view of a low noise rotor blade according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
A low-noise rotor blade aerodynamic profile for a helicopter, the main airfoil section of which comprises a plurality of airfoils, namely three airfoils of 12%, 9% and 7% of the same airfoil family, is divided into three blade sections. The first blade section adopts an airfoil profile which is 12% thicker than the first blade section, and the airfoil profile is arranged from the initial position of the blade airfoil profile to a relative radius of 0.65R-0.85R, preferably 0.78R; the second blade section is a transition section of 12% airfoil and 9% airfoil, wherein the 9% airfoil is arranged between relative radii 0.85R-0.92R, preferably at 0.85R; the third blade section is a transition section of 9% airfoil and 7% airfoil, the 7% airfoil being located at a relative radius of 0.95R-1.0R, preferably arranged at the tip, i.e. 1.0R. The three-section airfoil profile thickness distribution can be adapted to transonic flow during high-speed flight while ensuring that the rotor wing has enough lift force, so that high-speed impulse noise is effectively weakened.
The chord length of the first blade section of the blade is C, preferably, C is 0.435 m; the chord length at the relative radius of 0.85R is 1C-1.5C, preferably 1.1C, and the chord length between the relative radius of 0.78R and 0.85R is linear transition; the ratio of the chord length of the blade tip to the chord length of the first blade section is 1/3-1/2, preferably 1/3, and the chord length between the relative radius of 0.85R and the blade tip is linear transition. Figure 1 shows the chord length distribution curve of the blade. The chord length is reduced at the oar tip, so that the transonic effect at the oar tip can be effectively weakened, and the effect of reducing high-speed pulse noise is achieved.
The first paddle section of the paddle is rectangular in shape; the second blade section is a forward-swept part, the forward-swept angle is-4 degrees to-15 degrees, the sign is used for distinguishing the forward sweep from the backward sweep, and preferably, the forward-swept angle is-6 degrees; the third blade section is a swept back part, the swept back angle is 10-30 degrees, and preferably, the swept back angle is 12 degrees. The front and back sweeping combined type blade design can effectively weaken the propeller vortex interference phenomenon of the rotor wing, thereby greatly reducing the propeller vortex interference noise.
The paddle adopts a linear pneumatic negative torsion design, the torsion rate is-10 degrees/R to-14 degrees/R, and preferably, the torsion rate is-11 degrees/R. Preferably, the third section of the blade can reduce the negative torsion rate as much as possible, even if the torsion rate is 0. The three-section torsion rate design can ensure that the rotor wing has enough hovering performance and a front flying lift-drag ratio. Preferably, 0 twist rate is used from the blade relative radius 0.9R to the tip. Preferably, 0 twist rate is used from the blade relative radius of 0.95R to the tip. So as to reduce the influence of the negative lift generated by the blade tip when the blade flies forward at a high speed. Figure 2 shows the twist angle profile of the blade.
FIG. 3 provides a schematic representation of the aerodynamic profile of a preferred embodiment blade.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. The utility model provides a helicopter low noise rotor blade aerodynamic profile which characterized in that: the main wing section of the helicopter rotor blade comprises three blade sections, wherein the three blade sections respectively adopt wing profiles with the relative thicknesses of 12%, 9% and 7% of the same wing profile family.
2. A helicopter low noise rotor blade aerodynamic profile according to claim 1, wherein: the airfoil profile of the first section of the blade section is 12% of the airfoil profile with relative thickness, and the 12% airfoil profile position is from the initial position of the airfoil profile of the blade to the position of 0.65R-0.85R of the relative radius;
the airfoil profile of the second blade section is a transition section of 12% airfoil profile and 9% airfoil profile; the 9% airfoil profile is arranged between the relative radiuses of 0.85R-0.92R;
the airfoil profile of the third section blade section is a transition section of 9% airfoil profile and 7% airfoil profile, and the 7% airfoil profile is arranged between the relative radiuses of 0.95R and 1.0R.
3. A helicopter low noise rotor blade aerodynamic profile according to claim 2, wherein: the 12% airfoil position is from the blade airfoil starting position to 0.78R of the relative radius;
the 9% airfoil was disposed at a relative radius of 0.85R;
the 7% airfoil is disposed at a relative radius of 1.0R.
4. A helicopter low noise rotor blade aerodynamic profile according to claim 2, wherein: the chord length of the first section of the blade is C;
the chord length of the 9 percent airfoil section is 1C-1.5C, and the chord length of the second section of blade section is in linear transition;
the chord length of the 7 percent airfoil section is 1/3-1/2C, and the chord length of the third section of blade section is in linear transition.
5. A helicopter low noise rotor blade aerodynamic profile according to claim 2, wherein: the first blade section is rectangular in shape;
the second section of blade section is in a forward swept shape, and the forward swept angle is-4 degrees to-15 degrees;
the third section of the blade section is in a sweepback shape, and the sweepback angle is 10-30 degrees.
6. A helicopter low noise rotor blade aerodynamic profile according to claim 5, wherein: the forward swept angle of the second section of the blade section is-6 degrees;
the sweepback angle of the third section of blade section is 12 degrees.
7. A helicopter low noise rotor blade aerodynamic profile according to claim 2, wherein: the paddle adopts a linear pneumatic negative torsion design, and the pneumatic torsion rate is-10 degrees/R to-14 degrees/R.
8. A helicopter low noise rotor blade aerodynamic profile according to claim 7, wherein: the pneumatic torsion rate of the blade is-11 degrees/R.
9. A helicopter low noise rotor blade aerodynamic profile according to claim 7, wherein: and the aerodynamic torsion ratio of the third section of the blade section is 0.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011028590.0A CN112173075B (en) | 2020-09-25 | 2020-09-25 | Aerodynamic profile of helicopter low-noise rotor blade |
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| CN202011028590.0A CN112173075B (en) | 2020-09-25 | 2020-09-25 | Aerodynamic profile of helicopter low-noise rotor blade |
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| CN112173075A true CN112173075A (en) | 2021-01-05 |
| CN112173075B CN112173075B (en) | 2022-12-30 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977814A (en) * | 2021-03-04 | 2021-06-18 | 南京航空航天大学 | Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft |
| WO2024093481A1 (en) * | 2022-11-01 | 2024-05-10 | 苏州览众科技有限公司 | Variable-rotating-speed rotor blade, coaxial unmanned helicopter, and single-rotor unmanned helicopter |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977814A (en) * | 2021-03-04 | 2021-06-18 | 南京航空航天大学 | Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft |
| CN112977814B (en) * | 2021-03-04 | 2022-03-08 | 南京航空航天大学 | Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft |
| WO2024093481A1 (en) * | 2022-11-01 | 2024-05-10 | 苏州览众科技有限公司 | Variable-rotating-speed rotor blade, coaxial unmanned helicopter, and single-rotor unmanned helicopter |
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| Publication number | Publication date |
|---|---|
| CN112173075B (en) | 2022-12-30 |
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