CN112977815A - Rotor craft, blade of rotor craft and wing section of blade - Google Patents

Rotor craft, blade of rotor craft and wing section of blade Download PDF

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Publication number
CN112977815A
CN112977815A CN202110507545.1A CN202110507545A CN112977815A CN 112977815 A CN112977815 A CN 112977815A CN 202110507545 A CN202110507545 A CN 202110507545A CN 112977815 A CN112977815 A CN 112977815A
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airfoil
blade
camber line
maximum
camber
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CN112977815B (en
Inventor
毛一年
周东岳
姜欣宏
初征
郜奥林
杨芳
刘金来
马聪
赵龙智
刘璐
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Beijing Sankuai Online Technology Co Ltd
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Beijing Sankuai Online Technology Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors

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  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present disclosure relates to a rotorcraft, a blade for a rotorcraft, and an airfoil profile therefor, wherein the airfoil profile is composed of a leading edge, a trailing edge, and an up-camber line and a down-camber line between the leading edge and the trailing edge, the airfoil profile having a maximum thickness
Figure 578525DEST_PATH_IMAGE001
Chord length of airfoil
Figure 385944DEST_PATH_IMAGE002
In a ratio of
Figure 353900DEST_PATH_IMAGE003
Maximum thickness is located at
Figure 184452DEST_PATH_IMAGE004
At least one of (1) and (b); maximum camber of an airfoil
Figure 568160DEST_PATH_IMAGE005
Chord length of airfoil
Figure 433348DEST_PATH_IMAGE006
In a ratio of
Figure 368943DEST_PATH_IMAGE007
Maximum camber
Figure 93317DEST_PATH_IMAGE008
Is located at
Figure 343032DEST_PATH_IMAGE009
At least one of (1) and (b); wherein the content of the first and second substances,
Figure 125044DEST_PATH_IMAGE010
is the distance along the chord from the leading edge to the trailing edge,
Figure 841327DEST_PATH_IMAGE011
、
Figure 380893DEST_PATH_IMAGE012
、
Figure 231037DEST_PATH_IMAGE013
have a maximum error of ± 3%, respectively. Through above-mentioned technical scheme, can provide higher lift-drag ratio for rotor craft under low reynolds number to improve rotor craft's aerodynamic efficiency. Furthermore, due to the improved aerodynamic efficiency of the rotorcraft, the required speed is lower with the same distribution of the lifting surfaces, making it possible to reduce the noise generated during the flight of the rotorcraft.

Description

Rotor craft, blade of rotor craft and wing section of blade
Technical Field
The present disclosure relates to the field of aircraft technology, and in particular, to a rotorcraft, a rotorcraft blade, and a rotorcraft airfoil.
Background
Improving aerodynamic efficiency is an important task in aircraft design. In the case of rotorcraft, it is necessary to reduce the power consumed as much as possible while generating the same lift, or to generate as much lift as possible while consuming the same power, which is of great importance for increasing the endurance, range and load-carrying capacity of the aircraft.
The wing profile is a two-dimensional section perpendicular to a leading edge of the rotor wing at any position in the spanwise direction, is a source for reflecting pressure difference generated on the upper surface and the lower surface of the rotor wing, and has important influence on the lift force or the thrust of the rotor wing, the aerodynamic noise and the performance of an aircraft. The existing wing profile is mainly designed for a large manned aircraft, the Reynolds number is generally over 1000,000, the size of a multi-rotor unmanned aerial vehicle on the market is small, the Reynolds number is low and is generally below 1000,000, the wing profile capable of providing excellent aerodynamic efficiency is less aiming at the aircraft with the characteristic, the lift coefficient and the lift-drag ratio are generally low under the low Reynolds number of the wing profile in the related technology, and the aerodynamic efficiency is lower.
Disclosure of Invention
A first object of the present disclosure is to provide an airfoil for a blade of a rotorcraft that enables to improve the aerodynamic efficiency of the craft.
To achieve the above objects, the present disclosure provides an airfoil for a blade of a rotary-wing aircraft, the airfoil being comprised of a leading edge, a trailing edge, and an up-camber line and a down-camber line therebetween, the airfoil having a maximum thickness
Figure DEST_PATH_IMAGE001
Chord length of airfoil
Figure 43990DEST_PATH_IMAGE002
In a ratio of
Figure DEST_PATH_IMAGE003
Said maximum thickness being located at
Figure 281067DEST_PATH_IMAGE004
At least one of (1) and (b); maximum camber of the airfoil
Figure DEST_PATH_IMAGE005
Chord length of airfoil
Figure 258250DEST_PATH_IMAGE006
In a ratio of
Figure DEST_PATH_IMAGE007
Said maximum camber
Figure 326701DEST_PATH_IMAGE008
Is located at
Figure DEST_PATH_IMAGE009
At least one of (1) and (b); wherein the content of the first and second substances,
Figure 668820DEST_PATH_IMAGE010
is the distance along the chord line from the leading edge to the trailing edge,
Figure DEST_PATH_IMAGE011
、
Figure 393194DEST_PATH_IMAGE012
、
Figure DEST_PATH_IMAGE013
have a maximum error of ± 3%, respectively.
Optionally, the camber line is defined by a camber line coordinate value pair
Figure 846172DEST_PATH_IMAGE013
，y u /cIs defined as aboveArc line coordinate value pair
Figure 565866DEST_PATH_IMAGE013
，y u /cAs defined below:
Figure 406783DEST_PATH_IMAGE014
wherein the content of the first and second substances,y u is the distance of the upper arc line perpendicular to the chord line, and the numerical value pair of the upper arc line coordinates
Figure 149611DEST_PATH_IMAGE013
，y u /cThe maximum error in each of these is equal to ± 3%.
Optionally, the camber line is bounded by camber line coordinate value pairs
Figure 734176DEST_PATH_IMAGE013
，y l /cDefined, the pair of lower arc coordinate values
Figure 980481DEST_PATH_IMAGE013
，y l /cAs defined below:
Figure DEST_PATH_IMAGE015
wherein the content of the first and second substances,y l is the distance of the lower arc line perpendicular to the chord line, and the numerical value pair of the lower arc line coordinates
Figure 398824DEST_PATH_IMAGE013
，y l /cThe maximum error in each of these is equal to ± 3%.
Optionally, the pair of camber line coordinate values
Figure 222424DEST_PATH_IMAGE013
，y u /cIs further defined in accordance with:
Figure 486046DEST_PATH_IMAGE016
optionally, the camber line coordinate values
Figure 914753DEST_PATH_IMAGE013
，y l /cIs further defined in accordance with:
Figure DEST_PATH_IMAGE017
optionally, the pair of camber line coordinate values
Figure 769577DEST_PATH_IMAGE013
，y u /cIs further defined in accordance with:
Figure 346052DEST_PATH_IMAGE018
optionally, the pair of arc camber coordinate values
Figure 475682DEST_PATH_IMAGE013
，y l /cIs further defined in accordance with:
Figure DEST_PATH_IMAGE019
a second object of the present disclosure is to provide a blade for a rotorcraft, said blade having an airfoil shape according to any one of the preceding claims.
Optionally, the number of the blades is at least two, and the two blades are integrally connected at the root of the blade and are centrosymmetric relative to the central point of the connection.
Optionally, the paddle is a low reynolds number paddle.
A third object of the present disclosure is to provide a rotorcraft comprising a blade according to any one of the preceding claims.
The present disclosure increases camber of the airfoil front by reasonably optimizing the airfoil, specifically, increasing the airfoil thickness and advancing the location of maximum thickness. The increase of the airfoil thickness is favorable for the airfoil to increase the maximum lift coefficient of the airfoil, the forward movement of the maximum airfoil thickness is favorable for vortex shedding and backflow at the rear part of the airfoil, particularly at the maximum attack angle, so that the aerodynamic efficiency is improved, and the camber of the front half part of the airfoil is increased within the range of the design lift coefficient, so that the incidence angle between the front edge and the airflow can be reduced. Through above-mentioned technical scheme, can provide higher lift-drag ratio for rotor craft under low reynolds number to improve rotor craft's aerodynamic efficiency. Furthermore, due to the improved aerodynamic efficiency of the rotorcraft, the required speed is lower with the same distribution of the lifting surfaces, making it possible to reduce the noise generated during the flight of the rotorcraft.
Additional features and advantages of the disclosure will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description serve to explain the disclosure without limiting the disclosure. In the drawings:
FIG. 1 is an illustration of various parameters of an airfoil provided by an exemplary embodiment of the present disclosure;
FIG. 2 is a schematic comparison of an airfoil provided by the present disclosure with a prior art airfoil;
FIG. 3 is a schematic view of a blade provided by an exemplary embodiment of the present disclosure.
Description of the reference numerals
1-blade, 11-leading edge, 12-trailing edge, 13-camber line, 14-camber line, 15-chord line, 16-root.
Detailed Description
The following detailed description of specific embodiments of the present disclosure is provided in connection with the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present disclosure, are given by way of illustration and explanation only, not limitation. The terms upper and lower equal orientation as presented in this embodiment are with reference to the rotor after it is mounted on the aircraft and the normal operational attitude of the rotorcraft, and should not be considered limiting.
The airfoil of the blade for a rotary-wing aircraft according to the present disclosure is described in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.
As shown in fig. 1 and 2, the present disclosure provides an airfoil for a blade of a rotary-wing aircraft, the airfoil being composed of a leading edge 11, a trailing edge 12, and an camber line 13 and a camber line 14 between the leading edge 11 and the trailing edge 12, the airfoil having a maximum thickness
Figure 227737DEST_PATH_IMAGE001
Chord length of airfoil
Figure 50199DEST_PATH_IMAGE002
In a ratio of
Figure 723757DEST_PATH_IMAGE020
Maximum thickness is located at
Figure 453816DEST_PATH_IMAGE004
At least one of (1) and (b); maximum camber of an airfoil
Figure 529219DEST_PATH_IMAGE005
Chord length of airfoil
Figure 319321DEST_PATH_IMAGE006
In a ratio of
Figure 542492DEST_PATH_IMAGE007
Maximum camber
Figure DEST_PATH_IMAGE021
Is located at
Figure 748345DEST_PATH_IMAGE022
At least one of (1) and (b); wherein the content of the first and second substances,
Figure 412676DEST_PATH_IMAGE010
is the distance from the leading edge 11 to the trailing edge 12 along the chord line 15,
Figure 108099DEST_PATH_IMAGE011
、
Figure 21829DEST_PATH_IMAGE012
、
Figure 93690DEST_PATH_IMAGE013
have a maximum error of + -3%, respectively, i.e. within a tolerance range of + -3% error
Figure 612527DEST_PATH_IMAGE011
、
Figure 10010DEST_PATH_IMAGE012
、
Figure DEST_PATH_IMAGE023
The profile of the airfoil is constructed to fall within the scope of the claimed disclosure.
It should be noted that the parameters related to the present disclosure are all defined in a manner common in the art, and taking the airfoil in fig. 2 as an example, the leading edge 11 is set as the origin to establish a coordinate system and the chord length
Figure 614298DEST_PATH_IMAGE002
I.e. the distance from the leading edge 11 to the trailing edge 12; maximum thickness
Figure 755430DEST_PATH_IMAGE001
The maximum distance between the upper camber line 13 and the lower camber line 14, perpendicular to the chord line 15, will be the maximum thickness
Figure 659932DEST_PATH_IMAGE001
Divided by chord length
Figure 900420DEST_PATH_IMAGE002
I.e. by
Figure 647796DEST_PATH_IMAGE011
Referred to as maximum relative thickness; maximum camber of
Figure 202405DEST_PATH_IMAGE005
Maximum distance between mean camber line and chord line 15, maximum camber
Figure 289310DEST_PATH_IMAGE005
Divided by chord length
Figure 497438DEST_PATH_IMAGE002
，
Figure 607476DEST_PATH_IMAGE012
Referred to as maximum relative camber.
With continued reference to FIG. 2, by comparing the airfoil provided by the present disclosure (labeled E382, shown in solid lines) with the airfoil provided by the prior art (labeled E376, shown in dashed lines), the airfoil of the present disclosure has an increased thickness and shifts in the location of the maximum thickness while increasing the camber of the airfoil's forward half. The increase of the airfoil thickness is favorable for the airfoil to increase the maximum lift coefficient of the airfoil, the forward movement of the maximum airfoil thickness is favorable for vortex shedding and backflow at the rear part of the airfoil, particularly at the maximum attack angle, so that the aerodynamic efficiency is improved, and the camber of the front half part of the airfoil is increased within the range of the design lift coefficient, so that the incidence angle between the front edge and the airflow can be reduced.
The beneficial effects of the airfoil of the present disclosure in improving aerodynamic efficiency of a rotary wing vehicle will be further illustrated below by comparative experiments on aerodynamics of the rotor (E382) of the present disclosure and the airfoil (E376) provided in the prior art at low reynolds number flow.
As shown in the following Table 1, Reynolds numbers Re of 4X 10 were selected respectively4、1.8×105、4×105、6×105And 8 × 105The lift-to-drag ratio of the airfoil (E382) of the present disclosure is compared to that of the airfoil (E376) provided by the prior art. Within the range of reynolds numbers chosen,the maximum lift coefficient of the airfoil of the present disclosure is greater than the maximum lift-drag ratio of the airfoil (E376) provided by the prior art, specifically, when Re =4 × 104When the airfoil profile (E382) is used, the maximum lift coefficient is improved by 14.91% compared with that of the airfoil profile (E376) provided by the prior art; when Re =1.8 × 105When the airfoil profile (E382) is used, the maximum lift coefficient is improved by 10.28% compared with that of the airfoil profile (E376) provided by the prior art; when Re =4 × 105When the airfoil profile (E382) is used, the maximum lift coefficient is improved by 18.37% compared with the airfoil profile (E376) provided by the prior art; when Re =6 × 105In time, the maximum lift coefficient of the airfoil profile (E382) is improved by 10.99% compared with that of the airfoil profile (E376) provided by the prior art; when Re =8 × 105The maximum lift coefficient of the airfoil (E382) of the present disclosure is improved by 16.31% over the airfoil (E376) provided by the prior art.
TABLE 1 Lift-drag ratio of two airfoils at different Reynolds numbers
Figure 824831DEST_PATH_IMAGE024
Based on the theoretical analysis and experimental verification, the rotorcraft has higher lift-drag ratio at low reynolds number flow (40000-. Furthermore, aerodynamic noise generated by the rotor at high speed is a major source of noise in rotorcraft. Because the improvement of rotor craft aerodynamic efficiency, under the condition that same lifting surface distributes, required rotational speed is lower, therefore can the effectual noise that reduces rotor craft flight in-process and produce, promotes user experience.
According to one embodiment of the present disclosure, as shown in table 2 below, the camber line 13b may be represented by a pair of camber line coordinate values
Figure 766242DEST_PATH_IMAGE013
，y u /cLimited, upper arcLine coordinate value pair
Figure 286216DEST_PATH_IMAGE013
，y u /cMay be defined according to the following:
table 2: characteristic point coordinates of upper surface of middle part of airfoil profile
Figure DEST_PATH_IMAGE025
Wherein the content of the first and second substances,y u is the distance between the upper arc line 13 and the chord line 15, and the numerical value pair of the upper arc line coordinates
Figure 742605DEST_PATH_IMAGE013
，y u /cThe maximum error in each of these is equal to ± 3%.
Further, the down arc 14b is represented by a pair of down arc coordinate values
Figure 639017DEST_PATH_IMAGE013
，y l /cDefined, down arc coordinate value pairs
Figure 497252DEST_PATH_IMAGE013
，y l /cAs defined below:
table 3: feature point coordinates of lower surface of middle part of airfoil profile
Figure 516023DEST_PATH_IMAGE015
Wherein the content of the first and second substances,y l is the distance of the lower arc line 14 perpendicular to the chord line 15, and the numerical value pair of the lower arc line coordinates
Figure 335075DEST_PATH_IMAGE013
，y l /cThe maximum error in each of these is equal to ± 3%.
The shape of the middle area of the airfoil, which is drawn according to the data in the above table, can refer to fig. 2 (solid line), the maximum thickness and the position of the maximum camber of the airfoil are both in the middle area of the airfoil, and theoretically, the positions of the maximum thickness and the maximum camber have an important influence on the aerodynamic performance of the airfoil, and therefore, the middle area of the airfoil is an important optimization area. As can be seen from fig. 2, compared with the existing E376 airfoil (dotted line), the airfoil of the present disclosure has a larger thickness and a forward maximum thickness, so as to facilitate vortex shedding and backflow at the rear half of the airfoil, especially at the maximum attack angle, to improve aerodynamic efficiency, while the camber of the front half of the airfoil is increased, within the range of the design lift coefficient, so as to reduce the attack angle between the leading edge and the airflow.
Numerical value pair of upper arc line 13a coordinates
Figure 894232DEST_PATH_IMAGE013
，y u /cIs further defined in accordance with:
table 4: coordinates of characteristic points of upper surface of front half part of airfoil profile
Figure 810235DEST_PATH_IMAGE016
Further, the down arc 14a coordinate value pair
Figure 937591DEST_PATH_IMAGE013
，y l /cIs further defined in accordance with:
table 5: coordinates of characteristic points of lower surface of front half part of airfoil profile
Figure 571835DEST_PATH_IMAGE017
Referring to fig. 2, the shape of the front half area of the airfoil drawn according to the data in the above table shows that the radius of the leading edge 11 is smaller, so that the airfoil is beneficial to reducing the windward area of the airfoil, and the pressure difference resistance is further reduced.
Numerical value pair of upper arc line 13c coordinates
Figure 934683DEST_PATH_IMAGE013
，y u /cIs further defined in accordance with:
table 6: coordinates of characteristic points on the rear half part of the airfoil
Figure 377297DEST_PATH_IMAGE018
Further, the down arc 14c coordinate value pair
Figure 737871DEST_PATH_IMAGE013
，y l /cIs further defined in accordance with:
table 7: characteristic point coordinates of lower surface of rear half part of airfoil
Figure 656149DEST_PATH_IMAGE019
Referring to fig. 2, the shape of the rear half area of the airfoil drawn according to the data in the above table shows that the trailing edge 12 adopts a sharpened design, so that the vortex at the trailing edge 12 can be weakened, the disturbance of the vortex can be reduced, and the noise can be reduced.
Camber line coordinate value pairs in this disclosure
Figure 432475DEST_PATH_IMAGE013
，y u /cAnd down arc line coordinate value pair
Figure 323070DEST_PATH_IMAGE013
，y l /cIs equal to + -3%, i.e., an upper arc coordinate pair within a tolerance of + -3% of the error
Figure 916863DEST_PATH_IMAGE013
，y u /cAnd down arc line coordinate value pair
Figure 260119DEST_PATH_IMAGE013
，y l /cThe profile of the enclosed airfoil falls within the scope of the protection claimed by the present disclosure, and the obtained airfoil still can obtain the beneficial effects of the airfoil within the error range. In addition, the coordinate pairs adopted when the airfoil profile is defined by the present disclosure are dimensionless coordinate values, and the shape of the airfoil is not changed when the data in the above tables 2 to 7 are subjected to scaling up or down.
The blade 1 of the present disclosure has any one of the above airfoils at different positions of its radial extension, and may be an airfoil in which the entire blade 1 (i.e., root to tip) has any one of the above airfoils, or an airfoil in which only one section has any one of the above airfoils, which is not limited by the present disclosure. Alternatively, the blade 1 has a plurality of blades 1, and the plurality of blades 1 are integrally connected at the root 16 and are centrosymmetric with respect to the center point position of the connection. A plurality of paddle 1 can integrated into one piece to can guarantee paddle 1's holistic structural strength, perhaps paddle 1 also can adopt the fashioned design of components of a whole that can function independently, for example, install each paddle 1 respectively on the propeller hub, make the installation and the change of paddle 1 comparatively convenient, the axis that the center of rotation of paddle 1 was the propeller hub place this moment. Fig. 3 shows an embodiment with three blades 1, which can reduce the rotational speed corresponding to the design drag, thus effectively reducing noise. Furthermore, the blade 1 of the present disclosure is suitable for rotorcraft with blade diameters between 0.3-3m and provides better aerodynamic efficiency at low reynolds numbers than existing airfoils.
A second object of the present disclosure is to provide a rotorcraft comprising a blade 1 according to any one of the preceding claims, and having all the advantages of the blade 1. Alternatively, the rotorcraft may be a multi-rotor aircraft.
The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.
It should be noted that the various features described in the above embodiments may be combined in any suitable manner without departing from the scope of the invention. In order to avoid unnecessary repetition, various possible combinations will not be separately described in this disclosure.
In addition, any combination of various embodiments of the present disclosure may be made, and the same should be considered as the disclosure of the present disclosure, as long as it does not depart from the spirit of the present disclosure.

Claims (11)

1. An airfoil for a blade of a rotorcraft, characterized in that it is composed of a leading edge (11), a trailing edge (12) and, between said leading edge (11) and trailing edge (12), an up-camber line (13) and a down-camber line (14), the maximum thickness of said airfoil being
Figure 832047DEST_PATH_IMAGE001
Chord length of airfoil
Figure 275798DEST_PATH_IMAGE002
In a ratio of
Figure 288753DEST_PATH_IMAGE003
Said maximum thickness being located at
Figure 905679DEST_PATH_IMAGE004
At least one of (1) and (b); maximum camber of the airfoil
Figure 664688DEST_PATH_IMAGE005
Chord length of airfoil
Figure 138394DEST_PATH_IMAGE002
In a ratio of
Figure 248433DEST_PATH_IMAGE006
Said maximum camber
Figure 403471DEST_PATH_IMAGE007
Is located at
Figure 407199DEST_PATH_IMAGE008
At least one of (1) and (b); wherein the content of the first and second substances,
Figure 661594DEST_PATH_IMAGE009
is the distance from the leading edge (11) to the trailing edge (12) in the direction of the chord line (15),
Figure 383562DEST_PATH_IMAGE010
、
Figure 14395DEST_PATH_IMAGE011
、
Figure 872629DEST_PATH_IMAGE012
have a maximum error of ± 3%, respectively.
2. Wing profile for a rotor-craft blade according to claim 1, characterised in that said camber line (13 b) is defined by a pair of camber line coordinate values
Figure 563505DEST_PATH_IMAGE012
，y u /cDefined, said pairs of upper arc coordinate values
Figure 710452DEST_PATH_IMAGE012
，y u /cAs defined below:
Figure 4030DEST_PATH_IMAGE013
wherein the content of the first and second substances,y u is the distance of the camber line (13) perpendicular to the chord line (15), and the camber line coordinate value pair
Figure 592138DEST_PATH_IMAGE014
，y u /cThe maximum error in each of these is equal to ± 3%.
3. Wing profile for a blade of a rotary-wing aircraft according to any one of claims 2, characterized in that said camber line (14 b) is defined by a pair of camber line coordinate values
Figure 578548DEST_PATH_IMAGE012
，y l /cDefined, the pair of lower arc coordinate values
Figure 150475DEST_PATH_IMAGE012
，y l /cAs defined below:
Figure 451006DEST_PATH_IMAGE015
wherein the content of the first and second substances,y l is the distance of the camber line (14) perpendicular to the chord line (15), the camber line coordinate value pair
Figure 283833DEST_PATH_IMAGE012
，y l /cThe maximum error in each of these is equal to ± 3%.
4. Airfoil profile for a blade of a rotary-wing aircraft according to claim 3, characterized in that said camber line (13 a) has a pair of coordinate values
Figure 644407DEST_PATH_IMAGE016
，y u /cIs further defined in accordance with:
Figure 703630DEST_PATH_IMAGE017
。
5. airfoil profile for a blade of a rotary-wing aircraft according to claim 4, characterized in that said camber line (14 a) has a numerical value of the coordinates
Figure 542273DEST_PATH_IMAGE012
，y l /cIs further defined in accordance with:
Figure 229607DEST_PATH_IMAGE018
。
6. airfoil profile for a blade of a rotary-wing aircraft according to claim 5, characterized in that said camber line (13c) has a pair of values of coordinates
Figure 757405DEST_PATH_IMAGE012
，y u /cIs further defined in accordance with:
Figure 897399DEST_PATH_IMAGE019
。
7. airfoil profile for a blade of a rotary-wing aircraft according to claim 6, characterized in that said camber line (14 c) coordinate value pair
Figure 477416DEST_PATH_IMAGE016
，y l /cIs further defined in accordance with:
Figure 284835DEST_PATH_IMAGE020
。
8. a blade for a rotary-wing aircraft, characterized in that the blade (1) has an airfoil profile according to any one of claims 1 to 7.
9. The rotorcraft blade according to claim 8, wherein the blade (1) has a plurality of blades (1) integrally connected at a root (16) and centrally symmetrical with respect to a central point of the connection.
10. The rotorcraft blade according to claim 8, wherein the blade (1) is a low reynolds number blade.
11. A rotary wing aircraft, characterized in that it comprises a blade according to any one of claims 8 to 10.
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