CN114228988A - High-thrust high-lift-drag-ratio propeller and propeller blade design method - Google Patents
High-thrust high-lift-drag-ratio propeller and propeller blade design method Download PDFInfo
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- CN114228988A CN114228988A CN202111420778.4A CN202111420778A CN114228988A CN 114228988 A CN114228988 A CN 114228988A CN 202111420778 A CN202111420778 A CN 202111420778A CN 114228988 A CN114228988 A CN 114228988A
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- 230000007704 transition Effects 0.000 claims description 4
- 239000000725 suspension Substances 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims description 2
- 238000010408 sweeping Methods 0.000 claims description 2
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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
- B64C27/467—Aerodynamic features
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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
- B64C27/463—Blade tips
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
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Abstract
The invention discloses a high-thrust high-lift-drag-ratio propeller and a design method of blades of the propeller, wherein the high-thrust high-lift-drag-ratio propeller comprises a hub and a plurality of blades connected with the hub, the blades comprise a plurality of section wing profiles from a blade root to a blade tip, the radius of each blade is R, the attack angle of each blade is 19-21 degrees at a position 0.25R away from the center of a rotating disk of each blade, and the chord length of each blade is 0.174R; at the position 0.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 16-19 degrees, and the chord length of the blade is 0.159R; at the position 0.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 14.2-16.2 degrees, and the chord length of the blade is 0.140R. The high-thrust high-lift-drag ratio propeller disclosed by the invention is at the same rotating speed, the force efficiency of the propeller is higher than that of the traditional propeller, the efficiency of the aircraft can be improved, and the endurance time of the aircraft is increased.
Description
Technical Field
The invention relates to the technical field of propellers of unmanned aerial vehicles, in particular to a propeller with high thrust and high lift-drag ratio and a design method of blades of the propeller.
Background
In the prior art, the application of many rotor unmanned aerial vehicle is more and more extensive, and the screw is the key part for many rotor crafts provide power, and the flight performance of aircraft to a great extent depends on the performance of screw. From the prior art, the design of the multi-rotor unmanned aerial vehicle propeller at home and abroad basically refers to the design idea of the propeller of a helicopter or a fixed wing, and is mainly based on the chord length and the attack angle of the maximum-efficiency propeller under the hovering working condition.
However, for the small-angle maneuvering flight working condition, the flow fields of the multi-rotor propeller and the fixed-wing aircraft propeller are obviously different, and the incidence-chord length propeller adopting the linear distribution design is low in efficiency. Therefore, special optimization design needs to be carried out for hovering and small-angle maneuvering flight, the efficiency of the propeller is improved, noise is reduced, the flight time is prolonged, and the experience of customers is improved.
Disclosure of Invention
The invention aims to: the propeller with the high thrust-to-high lift-drag ratio and the design method of the propeller blades solve the problems in the prior art, the airfoil distribution of each radial section of each blade is determined according to the hovering working condition and the small-angle flat flying working condition, and the power efficiency of the propeller is higher than that of the traditional propeller at the same rotating speed, so that the efficiency of an aircraft is improved, and the endurance time of the aircraft is prolonged.
The technical scheme of the invention is as follows:
the utility model provides a high thrust high lift-drag ratio screw which characterized in that: the multi-blade wind power generation device comprises a hub and a plurality of blades connected with the hub, wherein the blades comprise a plurality of section wing profiles from a blade root to a blade tip, the radius of each blade is R,
at the position 0.25R away from the center of the rotating disc of the blade, the attack angle of the blade is 19-21 degrees, and the chord length of the blade is 0.174R;
at the position 0.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 16-19 degrees, and the chord length of the blade is 0.159R;
at the position 0.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 14.2-16.2 degrees, and the chord length of the blade is 0.140R;
at the position 0.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 11-13 degrees, and the chord length of the blade is 0.118R;
at the position 0.82R away from the center of the rotating disc of the blade, the attack angle of the blade is 7.7-9.7 degrees, and the chord length of the blade is 0.092R;
at the position 0.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 4.5-6.5 degrees, and the chord length of the blade is 0.069R;
at the position R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 0.041R.
As a further improvement of the scheme, at the position 0.25R away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 0.174R;
at the position 0.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 0.159R;
at the position 0.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 15.2 degrees, and the chord length of the blade is 0.140R;
at the position 0.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 0.118R;
at the position 0.82R away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 0.092R;
at the position 0.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 5.5 degrees, and the chord length of the blade is 0.069R;
at a distance R from the center of the rotating disc of the blade, the attack angle of the blade is 0.3 degrees, and the chord length of the blade is 0.041R.
As a further improvement of the scheme, the radius of the paddle is 266.7mm, and the diameter is 533.4 mm;
at the position 66.7mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 19-21 degrees, and the chord length of the paddle is 46.5 mm;
at a position 106.7mm away from the center of a rotating disk of the blade, the attack angle of the blade is 17-19 degrees, and the chord length of the blade is 42.4 mm;
at the position 146.7mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 14.2-16.2 degrees, and the chord length of the paddle is 37.3 mm;
the attack angle of the paddle is 11-13 degrees at the position 181.4mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 31.5 mm;
the attack angle of the paddle is 7.7-9.7 degrees at the position 218.7mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 24.6 mm;
at a position 248.0mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 4.5-6.5 degrees, and the chord length of the paddle is 18.3 mm;
at the position R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 11 mm.
As a further improvement of the scheme, the radius of the paddle is 266.7mm, and the diameter is 533.4 mm;
at a position 66.7mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm;
at a position 106.7mm away from the center of a rotating disk of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm;
at a position 146.7mm away from the center of the rotating disc of the blade, the attack angle of the blade is 15.2 degrees, and the chord length of the blade is 37.3 mm;
the attack angle of the blade is 12 degrees at the position 181.4mm away from the center of the rotating disk of the blade, and the chord length of the blade is 31.5 mm;
the attack angle of the blade is 8.7 degrees at the position 218.7mm away from the center of the rotating disk of the blade, and the chord length of the blade is 24.6 mm;
at a position 248.0mm away from the center of a rotating disc of the blade, the attack angle of the blade is 5.5 degrees, and the chord length of the blade is 18.3 mm;
the attack angle of the blade is 0.3 degrees at a position 266.7mm away from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
As a further improvement of the scheme, the attack angle of the paddle is 20 degrees at a position 70mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 46.5 mm;
at the position 110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm;
the attack angle of the paddle is 15.2 degrees at a position 148mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm;
at a position 187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm;
at a position 225mm away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm;
at 253mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 5.5 degrees, and the chord length of the paddle is 18.3 mm;
the attack angle of the blade is 0.3 degrees at 271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
As a further improvement of the scheme, the tip of the propeller adopts a downward reverse or/and backward sweeping structure.
As a further improvement of the scheme, the blade tip adopts a downward reverse angle of 23 degrees, and the blade tip vortex generating position of the downward reverse blade tip is lower than that of the rotor blade disc.
As a further improvement of the scheme, the paddle blade comprises a paddle root step, a paddle root transition section, a front edge, a rear edge, an upper surface and a lower surface which extend outwards along the radial direction in sequence from the paddle root to the paddle tip.
A design method for propeller blades with high thrust and high lift-drag ratio is characterized by comprising the following steps: which comprises the following steps:
determining the number n of blades and the radius R of a spiral, and dividing the blades into m sections, wherein the blades are divided into m +1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, calculating the attack angle of each section airfoil and the chord length of each section of blade;
in order to ensure that the propeller has enough tension in a hovering state and high efficiency in forward flight, the attack angle and the chord length of the propeller are designed according to a hovering working condition and a small-angle flat flight working condition respectively, the attack angle adopts the attack angle calculated in the forward flight, the chord length adopts the chord length calculated in the suspension, the attack angle is reduced nonlinearly from the root part of the blade to the tip part of the blade, the chord length is increased firstly and then gradually reduced;
fifthly, the blade tip adopts a downward-backward or/and backward-swept structure, and the front edge and the rear edge of the blade are connected by curves.
As a further improvement of the scheme, the design method of the propeller blade with high thrust and high lift-drag ratio comprises the following steps:
determining the number of blades to be three and the spiral radius to be 271.5mm, and dividing the blades into 7 sections, so that the blades are divided into 7+1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, at the position 70mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm; at the position 110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm; the attack angle of the paddle is 15.2 degrees at a position 148mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm; at a position 187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm; at a position 225mm away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm; at 253mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 5.5 degrees, and the chord length of the paddle is 18.3 mm; the attack angle of the blade is 0.3 degrees at 271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
The invention has the advantages that:
1. the high-thrust high-lift-drag-ratio propeller disclosed by the invention respectively determines the wing profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition, and the force efficiency of the propeller is higher than that of the traditional propeller at the same rotating speed, so that the efficiency of an aircraft is improved, and the endurance time of the aircraft is prolonged.
2. The propeller tip of the propeller adopts a structure of downward reverse and backward sweep, and the vortex intensity at the propeller tip can be reduced, so that the air resistance of the propeller tip is reduced, and the speed can reach the best when the aircraft uses the propeller to fly.
3. According to the design method of the propeller blade with high thrust and high lift-drag ratio, disclosed by the invention, the wing profile distribution of each section along the radial direction of the blade is respectively determined according to the hovering working condition and the small-angle flat flight working condition, and the force effect of the blade is higher than that of the traditional blade under the same rotating speed, so that the efficiency of an aircraft is improved, and the endurance time of the aircraft is increased.
Drawings
The invention is further described with reference to the following figures and examples:
FIG. 1 is a schematic view of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 2 is a schematic view A-A of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 3 is a schematic view B-B of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 4 is a schematic C-C view of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 5 is a schematic view of the high thrust high lift to drag ratio propeller blades of the present invention taken from D-D.
FIG. 6 is a schematic view E-E of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 7 is a schematic view F-F of the high thrust high lift to drag ratio propeller blades of the present invention.
FIG. 8 is a schematic view of the high thrust high lift to drag ratio propeller blades of the present invention taken from the perspective of G-G.
FIG. 9 is a schematic view of a further angle of the high thrust to high lift to drag ratio propeller blades of the present invention.
Wherein: 1. the blade rotating disc comprises a blade rotating disc center 2, a blade root step 3, a blade root transition section 4, a blade tip 5, a front edge 6, an upper surface 7 and a rear edge.
Detailed Description
The technical solution of the present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments.
As shown in fig. 1-9, the invention discloses a high-thrust high-lift-drag-ratio propeller, which comprises a hub and a plurality of blades connected with the hub, wherein the blades comprise a plurality of section wing profiles from a blade root to a blade tip 4, the radius of the blades is R, the attack angle of the blades is 19-21 degrees at a position 10.25R away from the center of a rotating disk of the blades, and the chord length of the blades is 0.174R; at the position 10.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 16-19 degrees, and the chord length of the blade is 0.159R; at the position 10.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 14.2-16.2 degrees, and the chord length of the blade is 0.140R; at the position 10.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 11-13 degrees, and the chord length of the blade is 0.118R; at the position 10.82R away from the center of the rotating disc of the blade, the attack angle of the blade is 7.7-9.7 degrees, and the chord length of the blade is 0.092R; at the position 10.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 4.5-6.5 degrees, and the chord length of the blade is 0.069R; at the position 1R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 0.041R. The high-thrust high-lift-drag-ratio propeller disclosed by the invention respectively determines the wing profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition, and the force efficiency of the propeller is higher than that of the traditional propeller at the same rotating speed, so that the efficiency of an aircraft is improved, and the endurance time of the aircraft is prolonged.
As a further improvement of the scheme, the attack angle of the blade is 20 degrees at a position 10.25R away from the center of the rotating disc of the blade, and the chord length of the blade is 0.174R; at a position 10.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 0.159R; at a position 10.55R away from the center of a rotating disc of the blade, the attack angle of the blade is 15.2 degrees, and the chord length of the blade is 0.140R; at a position 10.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 0.118R; at a position 10.82R away from the center of a rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 0.092R; at a position 10.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 5.5 degrees, and the chord length of the blade is 0.069R; at a distance of 1R from the center of the rotating disc of the blade, the attack angle of the blade is 0.3 degrees, and the chord length of the blade is 0.041R. The method improves the load distribution of the blades at the sections with different radiuses under the hovering flight condition, ensures that the velocity components of the wake flow of the section from the blade section B to the section E in the axial direction of the propeller are basically consistent, ensures that the incidence angle distribution from the section E to the section G better meets the condition that the incidence angle of the incoming flow near the blade tip under the hovering condition is smaller, meets the optimal theoretical design requirement of the propeller, and maximizes the efficiency of the blades under the hovering condition.
As a further improvement of the scheme, the radius of the paddle is 266.7mm, and the diameter is 533.4 mm; at the position 166.7mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 19-21 degrees, and the chord length of the paddle is 46.5 mm; the attack angle of the paddle is 17-19 degrees at the position 1106.7mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 42.4 mm; the attack angle of the paddle is 14.2-16.2 degrees at the position 1146.7mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm; the attack angle of the paddle is 11-13 degrees at the position 1181.4mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 31.5 mm; the attack angle of the paddle is 7.7-9.7 degrees at the position 1218.7mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 24.6 mm; the attack angle of the paddle is 4.5-6.5 degrees at 1248.0mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 18.3 mm; at the position 1R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 11 mm. The method improves the load distribution of the blades at the sections with different radiuses under the hovering flight condition, ensures that the velocity components of the wake flow of the section from the blade section B to the section E in the axial direction of the propeller are basically consistent, ensures that the incidence angle distribution from the section E to the section G better meets the condition that the incidence angle of the incoming flow near the blade tip under the hovering condition is smaller, meets the optimal theoretical design requirement of the propeller, and maximizes the efficiency of the blades under the hovering condition.
As a further improvement of the scheme, the radius of the paddle is 266.7mm, and the diameter is 533.4 mm; at the position 166.7mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm; the attack angle of the blade is 18 degrees at the position 1106.7mm away from the center of the rotating disk of the blade, and the chord length of the blade is 42.4 mm; the attack angle of the blade is 15.2 degrees at the position 1146.7mm away from the center of the rotating disc of the blade, and the chord length of the blade is 37.3 mm; the attack angle of the blade is 12 degrees at the position 1181.4mm away from the center of the rotating disk of the blade, and the chord length of the blade is 31.5 mm; the attack angle of the blade is 8.7 degrees at the position 1218.7mm away from the center of the rotating disk of the blade, and the chord length of the blade is 24.6 mm; the attack angle of the blade is 5.5 degrees at the position 1248.0mm away from the center of the rotating disk of the blade, and the chord length of the blade is 18.3 mm; at a distance of 1R from the center of the rotating disc of the blade, the attack angle of the blade is 0.3 degrees, and the chord length of the blade is 11 mm. The method improves the load distribution of the blades at the sections with different radiuses under the hovering flight condition, ensures that the velocity components of the wake flow of the section from the blade section B to the section E in the axial direction of the propeller are basically consistent, ensures that the incidence angle distribution from the section E to the section G better meets the condition that the incidence angle of the incoming flow near the blade tip under the hovering condition is smaller, meets the optimal theoretical design requirement of the propeller, and maximizes the efficiency of the blades under the hovering condition.
As a further improvement of the scheme, the attack angle of the paddle is 20 degrees at a position 170mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 46.5 mm; at a position 1110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm; the attack angle of the blade is 15.2 degrees at a position 1148mm away from the center of the rotating disk of the blade, and the chord length of the blade is 37.3 mm; at a position 1187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm; at a position 1225mm away from the center of a rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm; the attack angle of the paddle is 5.5 degrees at a position 1253mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 18.3 mm; the attack angle of the blade is 0.3 degrees at 1271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm. The method improves the load distribution of the blades at the sections with different radiuses under the hovering flight condition, ensures that the velocity components of the wake flow of the section from the blade section B to the section E in the axial direction of the propeller are basically consistent, ensures that the incidence angle distribution from the section E to the section G better meets the condition that the incidence angle of the incoming flow near the blade tip under the hovering condition is smaller, meets the optimal theoretical design requirement of the propeller, and maximizes the efficiency of the blades under the hovering condition.
As a further improvement of the scheme, the blade tip 4 adopts a downward reverse angle of 23 degrees, and the blade tip vortex generating position of the downward reverse blade tip 4 is lower than that of the rotor blade disc, so that the distance from the blade tip vortex to the blade disc is increased, and the interference effect of the blade tip vortex on the rotor blade can be weakened. And as the dihedral angle increases, the vertical distance from the tip vortex to the disk increases, thereby reducing aerodynamic noise. The tip of the propeller adopts a downward-reverse or/and backward-swept structure, and the backward-swept or/and downward-reverse design of the tip of the propeller can reduce the strength of vortex at the tip of the propeller, so that the air resistance of the tip of the propeller is reduced, and the speed of an aircraft can reach the best when the aircraft flies by using the propeller.
As a further improvement of the scheme, the blade comprises a blade root step 2, a blade root transition section 2, a front edge, a rear edge 7, an upper surface 6 and a lower surface which extend outwards along the radial direction in sequence from the blade root to the blade tip 4.
A design method for propeller blades with high thrust and high lift-drag ratio is characterized by comprising the following steps: which comprises the following steps:
determining the number n of blades and the radius R of a spiral, and dividing the blades into m sections, wherein the blades are divided into m +1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, calculating the attack angle of each section airfoil and the chord length of each section of blade;
in order to ensure that the propeller has enough tension in a hovering state and high efficiency in forward flight, the attack angle and the chord length of the propeller are designed according to a hovering working condition and a small-angle flat flight working condition respectively, the attack angle adopts the attack angle calculated in the forward flight, the chord length adopts the chord length calculated in the suspension, the attack angle is reduced nonlinearly from the root part of the blade to the tip part of the blade, the chord length is increased firstly and then gradually reduced;
fifthly, the blade tip adopts a downward-backward or/and backward-swept structure, and the front edge and the rear edge of the blade are connected by curves.
As a further improvement of the scheme, the design method of the propeller blade with high thrust and high lift-drag ratio comprises the following steps:
determining the number of blades to be three and the spiral radius to be 271.5mm, and dividing the blades into 7 sections, so that the blades are divided into 7+1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, at the position 70mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm; at the position 110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm; the attack angle of the paddle is 15.2 degrees at a position 148mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm; at a position 187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm; at a position 225mm away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm; at 253mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 5.5 degrees, and the chord length of the paddle is 18.3 mm; the attack angle of the blade is 0.3 degrees at 271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm. According to the design method of the propeller blade with high thrust and high lift-drag ratio, disclosed by the invention, the wing profile distribution of each section along the radial direction of the blade is respectively determined according to the hovering working condition and the small-angle flat flight working condition, and the force effect of the blade is higher than that of the traditional blade under the same rotating speed, so that the efficiency of an aircraft is improved, and the endurance time of the aircraft is increased.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the invention. The present invention is not to be limited by the specific embodiments disclosed herein, and other embodiments that fall within the scope of the claims of the present application are intended to be within the scope of the present invention. The invention has various embodiments, and all technical solutions formed by adopting equivalent transformation or equivalent transformation are within the protection scope of the invention.
Claims (10)
1. The utility model provides a high thrust high lift-drag ratio screw which characterized in that: the multi-blade wind power generation device comprises a hub and a plurality of blades connected with the hub, wherein the blades comprise a plurality of section wing profiles from a blade root to a blade tip, the radius of each blade is R,
at the position 0.25R away from the center of the rotating disc of the blade, the attack angle of the blade is 19-21 degrees, and the chord length of the blade is 0.174R;
at the position 0.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 16-19 degrees, and the chord length of the blade is 0.159R;
at the position 0.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 14.2-16.2 degrees, and the chord length of the blade is 0.140R;
at the position 0.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 11-13 degrees, and the chord length of the blade is 0.118R;
at the position 0.82R away from the center of the rotating disc of the blade, the attack angle of the blade is 7.7-9.7 degrees, and the chord length of the blade is 0.092R;
at the position 0.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 4.5-6.5 degrees, and the chord length of the blade is 0.069R;
at the position R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 0.041R.
2. The high-thrust high-lift-ratio propeller of claim 1, wherein: at the position 0.25R away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 0.174R;
at the position 0.40R away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 0.159R;
at the position 0.55R away from the center of the rotating disc of the blade, the attack angle of the blade is 15.2 degrees, and the chord length of the blade is 0.140R;
at the position 0.68R away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 0.118R;
at the position 0.82R away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 0.092R;
at the position 0.93R away from the center of the rotating disc of the blade, the attack angle of the blade is 5.5 degrees, and the chord length of the blade is 0.069R;
at a distance R from the center of the rotating disc of the blade, the attack angle of the blade is 0.3 degrees, and the chord length of the blade is 0.041R.
3. The high-thrust high-lift-ratio propeller of claim 1, wherein: the radius of the blade is 266.7mm, and the diameter is 533.4 mm;
at the position 66.7mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 19-21 degrees, and the chord length of the paddle is 46.5 mm;
at a position 106.7mm away from the center of a rotating disk of the blade, the attack angle of the blade is 17-19 degrees, and the chord length of the blade is 42.4 mm;
at the position 146.7mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 14.2-16.2 degrees, and the chord length of the paddle is 37.3 mm;
the attack angle of the paddle is 11-13 degrees at the position 181.4mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 31.5 mm;
the attack angle of the paddle is 7.7-9.7 degrees at the position 218.7mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 24.6 mm;
at a position 248.0mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 4.5-6.5 degrees, and the chord length of the paddle is 18.3 mm;
at the position R away from the center of the rotating disc of the blade, the attack angle of the blade is 0-1.3 degrees, and the chord length of the blade is 11 mm.
4. The high-thrust high-lift-ratio propeller of claim 3, wherein: the radius of the blade is 266.7mm, and the diameter is 533.4 mm;
at a position 66.7mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm;
at a position 106.7mm away from the center of a rotating disk of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm;
at a position 146.7mm away from the center of the rotating disc of the blade, the attack angle of the blade is 15.2 degrees, and the chord length of the blade is 37.3 mm;
the attack angle of the blade is 12 degrees at the position 181.4mm away from the center of the rotating disk of the blade, and the chord length of the blade is 31.5 mm;
the attack angle of the blade is 8.7 degrees at the position 218.7mm away from the center of the rotating disk of the blade, and the chord length of the blade is 24.6 mm;
at a position 248.0mm away from the center of a rotating disc of the blade, the attack angle of the blade is 5.5 degrees, and the chord length of the blade is 18.3 mm;
the attack angle of the blade is 0.3 degrees at a position 266.7mm away from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
5. The high-thrust high-lift-ratio propeller of claim 1, wherein: at the position 70mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm;
at the position 110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm;
the attack angle of the paddle is 15.2 degrees at a position 148mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm;
at a position 187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm;
at a position 225mm away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm;
at 253mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 5.5 degrees, and the chord length of the paddle is 18.3 mm;
the attack angle of the blade is 0.3 degrees at 271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
6. The high-thrust high-lift-ratio propeller of claim 1, wherein: the tip of the propeller adopts a downward reverse or/and backward sweeping structure.
7. The high-thrust high-lift-drag-ratio propeller of claim 6, wherein: the blade tip adopts a downward reverse angle of 23 degrees, and the blade tip vortex generating position of the downward reverse blade tip is lower than the rotor blade disc.
8. The high-thrust high-lift-ratio propeller of claim 1, wherein: the paddle comprises a paddle root step, a paddle root transition section, a front edge, a rear edge, an upper surface and a lower surface which extend outwards along the radial direction in sequence between the paddle root and the paddle tip.
9. A design method for propeller blades with high thrust and high lift-drag ratio is characterized by comprising the following steps: which comprises the following steps:
determining the number n of blades and the radius R of a spiral, and dividing the blades into m sections, wherein the blades are divided into m +1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, calculating the attack angle of each section airfoil and the chord length of each section of blade;
in order to ensure that the propeller has enough tension in a hovering state and high efficiency in forward flight, the attack angle and the chord length of the propeller are designed according to a hovering working condition and a small-angle flat flight working condition respectively, the attack angle adopts the attack angle calculated in the forward flight, the chord length adopts the chord length calculated in the suspension, the attack angle is reduced nonlinearly from the root part of the blade to the tip part of the blade, the chord length is increased firstly and then gradually reduced;
fifthly, the blade tip adopts a downward-backward or/and backward-swept structure, and the front edge and the rear edge of the blade are connected by curves.
10. The method for designing a high-thrust high-lift-drag ratio propeller blade of claim 9, wherein: which comprises the following steps:
determining the number of blades to be two, three, four or five, the spiral radius to be 271.5mm, and dividing the blades into 7 sections, so that the blades are divided into 7+1 sections;
secondly, determining the airfoil profile distribution of each section along the radial direction of the blade according to the hovering working condition and the small-angle flat flying working condition;
thirdly, at the position 70mm away from the center of the rotating disc of the blade, the attack angle of the blade is 20 degrees, and the chord length of the blade is 46.5 mm; at the position 110mm away from the center of the rotating disc of the blade, the attack angle of the blade is 18 degrees, and the chord length of the blade is 42.4 mm; the attack angle of the paddle is 15.2 degrees at a position 148mm away from the center of the rotating disc of the paddle, and the chord length of the paddle is 37.3 mm; at a position 187mm away from the center of the rotating disc of the blade, the attack angle of the blade is 12 degrees, and the chord length of the blade is 31.5 mm; at a position 225mm away from the center of the rotating disc of the blade, the attack angle of the blade is 8.7 degrees, and the chord length of the blade is 24.6 mm; at 253mm away from the center of the rotating disc of the paddle, the attack angle of the paddle is 5.5 degrees, and the chord length of the paddle is 18.3 mm; the attack angle of the blade is 0.3 degrees at 271.5mm from the center of the rotating disc of the blade, and the chord length of the blade is 11 mm.
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