CN112161776A - Device and method for measuring airfoil lift force - Google Patents
Device and method for measuring airfoil lift force Download PDFInfo
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- CN112161776A CN112161776A CN202010962467.XA CN202010962467A CN112161776A CN 112161776 A CN112161776 A CN 112161776A CN 202010962467 A CN202010962467 A CN 202010962467A CN 112161776 A CN112161776 A CN 112161776A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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Abstract
The invention discloses a device for measuring airfoil lift force, which is used for being placed in a wind tunnel, and comprises: the two bearings are oppositely arranged and are respectively sleeved on the two linear guide rails, and after the wing profile is subjected to upward or downward lifting force in the wind tunnel, the wing profile drives the bearings to move upwards or downwards along the linear guide rails, so that the upward or downward displacement value of the wing profile is measured, and the lifting force of the wing profile is obtained; the invention is simple, reliable and visual; the invention does not need a wind tunnel balance, thereby reducing the experiment cost; the invention can change the attack angle of the airfoil by arranging the motor, and can measure a plurality of groups of data.
Description
Technical Field
The invention belongs to the field of airfoil testing equipment, and particularly relates to a device and a method for measuring airfoil lift force.
Background
The airfoil profile refers to a section perpendicular to the leading edge on an airplane wing, a tail wing, a missile wing surface, a helicopter rotor blade and a propeller blade. For an airplane, the wing profile is an important component forming a wing and a tail wing, and directly determines the aerodynamic performance and the flight quality of the airplane.
In wind tunnel experiments, common airfoil test means include an airfoil surface pressure measurement method and a balance force measurement method.
The pressure measurement method is that a series of pressure measurement holes are arranged on the surface of a model, and the lifting force and the moment of the model are obtained through the integration of surface pressure. The pressure measurement method for measuring the aerodynamic force of the airfoil profile has the following defects:
1. a large number of pressure measuring tubes need to be connected before the experiment, so that the time cost is high;
2. in the test process, the pressure measured on the surface needs to be converted into a pressure coefficient, and then the aerodynamic coefficient is obtained through integration, so that the result is not visual.
The force measurement method is to use a force measuring balance to obtain the aerodynamic force of a model. The use of a balance to measure airfoil aerodynamic forces has the following disadvantages:
1. the balance belongs to precision measurement equipment and is easy to damage in the using process;
2. the balance needs to be calibrated before use, and the process is relatively complicated.
The two methods cannot meet the requirements of simple, rapid and visual quantitative demonstration of the wing profile lift force.
Disclosure of Invention
The invention aims to provide a device and a method for measuring airfoil lift force, and aims to solve the problems of long time, complex process, high cost and non-intuitive measurement result in the measurement of airfoil lift force.
The invention adopts the following technical scheme: a device for measuring airfoil lift for placement in a wind tunnel, comprising:
two first upright posts are oppositely and vertically arranged,
two upper flat plates which are horizontally arranged and respectively fixed at the upper ends of the corresponding first upright posts,
two lower flat plates which are horizontally arranged and respectively fixed at the lower ends of the corresponding first upright posts,
two linear guide rails are vertically and oppositely arranged, two ends of each linear guide rail are respectively fixed on the corresponding upper flat plate and the corresponding lower flat plate,
two bearings which are oppositely arranged and respectively sleeved on the two linear guide rails are respectively used for fixing two ends of the wing section, so that the wing section is horizontally fixed between the two bearings,
two upper springs respectively sleeved on the upper half part of the linear guide rail, the upper ends of the upper springs are fixed, the lower ends of the upper springs are propped against the upper ends of the corresponding side bearings,
two lower springs are respectively sleeved on the lower half parts of the linear guide rails, the lower ends of the lower springs are fixed, the upper ends of the lower springs are propped against the lower ends of the corresponding side bearings,
the two bearings are also used for driving the bearings to move upwards or downwards along the linear guide rail after the wing profile is subjected to the upwards or downwards lifting force in the wind tunnel, so that the upwards or downwards displacement value of the wing profile is measured, and the lifting force of the wing profile is obtained.
Further, still include two relative and vertical second stands that set up, dull and stereotyped one end respectively with the upper end fixed connection of first stand on two, the other end respectively with the upper end fixed connection of the second stand that corresponds, dull and stereotyped one end respectively with the lower extreme fixed connection of first stand under two, the other end respectively with the lower extreme fixed connection of the second stand that corresponds, two first stands, two second stands, two last flat boards, two flat board are mutually supported down and are constituteed two relative frame type regions, two frame type regions all are used for holding linear guide, a bearing, the upper spring, lower spring.
Furthermore, an upper support plate and a lower support plate are fixedly connected between a first upright and a second upright which are located in the same frame type region, two ends of each of the two upper support plates and the two lower support plates are fixedly connected with the inner sides of the corresponding first upright and the corresponding second upright respectively, the two upper support plates and the two lower support plates are arranged in parallel with the upper flat plate, two ends of each of the two linear guide rails are fixed on the corresponding upper support plate and the corresponding lower support plate respectively, the first upright, the second upright, the upper support plates and the lower support plates which are located in the same frame type region are matched with each other to form a containing space, and the containing space is used for containing the linear guide rails, a bearing, an upper spring and a.
Further, a bearing is fixedly connected with a motor, an output shaft of the motor is mutually sleeved with a shaft of the wing profile, and the motor is used for rotating the wing profile through the shaft of the wing profile so as to change the attack angle of the wing profile.
Furthermore, another bearing is fixed the one end of wing section through the mounting, mounting and the bearing fixed connection that corresponds, and the wing section is fixed through the axle of fixed wing section to the mounting and motor mutually support.
Furthermore, a ruler is pasted on any one of the two first vertical columns or the two second vertical columns from top to bottom, a horizontally arranged pointer is fixedly connected to any one bearing, the pointer and the ruler are arranged oppositely, the pointer is used for marking the upward or downward displacement value of the bearing, and the lift force of the airfoil is obtained by reading the value.
Further, still fixedly connected with entablature between two last flat boards, still fixedly connected with bottom end rail between two lower flat boards, entablature, bottom end rail, two first stands, two second stands mutually support and form the region that is used for holding the wing section.
Furthermore, the lower part of the lower cross beam is fixedly connected with a base, a level meter is installed on the base, and the base is used for supporting the whole device and is conveniently placed in the wind tunnel.
A method for measuring wing profile lifting force based on the device comprises the following steps:
two proper end plates are selected to be sleeved at the two ends of the wing profile, so that the end plates generate two-dimensional flow on the wing profile,
the two ends of the wing profile are respectively fixed between the two bearings,
the device for measuring the airfoil lift is placed in a wind tunnel,
reading the displacement value of the pointer up or down,
the motor is started to change the attack angle of the airfoil profile,
and reading the displacement value of the pointer upwards or downwards again until the measurement is finished.
The invention has the beneficial effects that: the invention is simple, reliable and visual; the invention does not need a wind tunnel balance, thereby reducing the experiment cost; the measuring result of the invention is concise and visual; the angle of attack of the airfoil profile can be changed by arranging the motor, and multiple groups of data can be measured; the invention can also be used for demonstrating the mechanism of airfoil lift generation and demonstrating the change rule of the airfoil lift along with the change of the attack angle, the wind speed and the like.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of one side of the motor of the present invention;
fig. 3 is a detail view at scale of the present invention.
Wherein: 1. a first upright post; 2. an upper flat plate; 3. a lower flat plate; 4. a linear guide rail; 5. a bearing; 6. an upper spring; 7. a lower spring; 8. a second upright post; 9. an upper support plate; 10. a lower support plate; 11. a fixing member; 12. a scale; 13. a pointer; 14. an upper cross beam; 15. a lower cross beam; 16. a base; 17. a motor; 18. an airfoil profile; 19. and an end plate.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention discloses a device for measuring airfoil lift force, which is used for being placed in a wind tunnel, and as shown in figure 1, the device comprises two first upright posts 1, two upper flat plates 2, two lower flat plates 3, two linear guide rails 4, two bearings 5, two upper springs 6 and two lower springs 7.
Two first upright posts 1 are oppositely and vertically arranged, two upper flat plates 2 are horizontally arranged, two upper flat plates 2 are respectively fixed at the upper ends of the corresponding first upright posts 1, two lower flat plates 3 are horizontally arranged, two lower flat plates 3 are respectively fixed at the lower ends of the corresponding first upright posts 1, two linear guide rails 4 are vertically and oppositely arranged, two ends of the two linear guide rails 4 are respectively fixed on the corresponding upper flat plates 2 and lower flat plates 3, two bearings 5 are oppositely arranged, two bearings 5 are respectively sleeved on the two linear guide rails 4, the two bearings 5 are respectively used for fixing two ends of a wing section 18, so that the wing section 18 is horizontally fixed between the two bearings 5, as shown in figure 2, two upper springs 6 are respectively sleeved on the upper half parts of the linear guide rails 4, the upper ends of the two upper springs 6 are fixed and the lower ends of the two upper springs 6 are abutted against the upper ends of the corresponding bearings 5, and two lower springs 7, the lower ends of the two lower springs 7 are fixed, the upper ends of the two lower springs are abutted against the lower ends of the corresponding side bearings 5, the two bearings 5 are also used for driving the bearings 5 to move upwards or downwards along the linear guide rail 4 by the wing profiles 18 after the wing profiles 18 are subjected to the upwards or downwards lifting force in the wind tunnel, and then the upwards or downwards displacement value of the wing profiles 18 is measured, and the lifting force of the wing profiles 18 is obtained.
According to the invention, the linear guide rail 4 is installed by arranging the two first upright posts 1, the two upper flat plates 2 and the two lower flat plates 3, the bearing 5 is sleeved on the linear guide rail 4, the bearing 5 can slide up and down along the linear guide rail 4 after being stressed, the wing section 18 is fixed between the two bearings 5, and when the bearing 5 moves upwards or downwards, the displacement value of the bearing 5 is measured, so that the lifting force of the wing section 18 can be obtained, the structure is simple and reliable, the obtained result is visual, the aerodynamic coefficient is obtained without integration, and the lifting force is obtained by conversion.
This device still includes two relative and vertical second stands 8 that set up, two last dull and stereotyped 2 one end respectively with first stand 1's upper end fixed connection, two last dull and stereotyped 2 other ends respectively with the second stand 8's that corresponds upper end fixed connection, two dull and stereotyped 3's one end respectively with first stand 1's lower extreme fixed connection down, two dull and stereotyped 3's the other end respectively with the second stand 8's that corresponds lower extreme fixed connection down, two first stands 1, two second stands 8, two last dull and stereotyped 2, two dull and stereotyped 3 mutually support down and constitute two relative frame type regions, two frame type regions all are used for holding linear guide 4, bearing 5, upper spring 6, lower spring 7.
Can seal the region that holds bearing 5 and linear guide 4 through setting up second stand 8 for linear guide 4 more firm installation, and then make measured data more accurate, through setting up second stand 8 moreover, make second stand 8 and first stand 1 mutually support, the device is compacter, complete, and convenient the removal ensures measuring result's accuracy.
Be located and all fixedly connected with between regional first stand 1 of same frame type and the second stand 8 go up extension board 9 and lower extension board 10, two go up extension board 9 and the inboard fixed connection of second stand 8 with corresponding first stand respectively with the both ends of lower extension board 10, two go up extension board 9 and lower extension board 10 and all with last dull and stereotyped 2 parallel arrangement, two linear guide 4's both ends are fixed respectively on corresponding last extension board 9 and lower extension board 10, be located regional first stand 1 of same frame type, second stand 8, it forms accommodation space to go up extension board 9 and lower extension board 10 mutually supporting, accommodation space is used for holding linear guide 4, bearing 5, go up spring 6, lower spring 7.
Because the lift force of the wing profile 18 is relatively small, the displacement value of the bearing 5 moving upwards or downwards is relatively small, so that the linear guide 4 with relatively long length is needed to fix the two ends of the linear guide 4 on the upper flat plate 2 and the lower flat plate 3, and the distance between the upper flat plate 2 and the lower flat plate 3 cannot be too small, because the wing profile 18 needs to be accommodated, the two ends of the linear guide 4 are fixed on the upper support plate 9 and the lower support plate 10 by arranging the upper support plate 9 and the lower support plate 10, so that the requirement of accommodating the wing profile 18 is met, the requirement of arranging the relatively short linear guide 4 is also met, and the cost is saved.
One of the bearings 5 is also fixedly connected with a motor 17, an output shaft of the motor 17 is sleeved with a shaft of the wing profile 18, and the motor 17 is used for rotating the wing profile 18 through the shaft of the wing profile 18 so as to change an attack angle of the wing profile 18 and further measure multiple groups of data; the magnitude of the lift experienced by the airfoil 18 at multiple angles can be measured to ensure the comprehensiveness of the final experimental results. If the motor 17 is not arranged, the wing profile 18 needs to be rotated manually for multiple times, the required attack angle of the wing profile 18 is obtained through manual rotation, the required attack angle of the wing profile 18 can be obtained through rotation of the motor 17 by arranging the motor 17, the measuring time is shortened, the operation is simple, and the operation is not complicated.
The other bearing 5 fixes one end of the wing profile 18 through a fixing piece 11, the fixing piece 11 is fixedly connected with the corresponding bearing 5, and the fixing piece 11 is matched with the motor 17 to fix the wing profile 18 through fixing the shaft of the wing profile 18. The shape of the fixing member 11 is not required here, and the shaft of the wing profile 18 may be fixed by a clip, or may be fixed by another method, as long as the shaft of the wing profile 18 is fixed and the wing profile 18 is fixed.
As shown in fig. 3, a scale 12 is adhered to any one of the two first columns 1 or the two second columns 8 from top to bottom, a pointer 13 is further fixedly connected to any one of the bearings 5, the pointer 13 and the scale 12 are arranged oppositely, the pointer 13 is used for marking an upward or downward displacement value of the bearing 5, and the magnitude of the lift force of the airfoil 18 is obtained by reading a numerical value. The displacement value of the bearing 5 upwards or downwards can be observed from the outside of the wind tunnel very quickly by arranging the scale 12 and the pointer 13, so that the lift force of the wing section 18 is judged, the operation is convenient, and the reading is accurate.
Still fixedly connected with entablature 14 between two last flat board 2, still fixedly connected with bottom end rail 15 between two lower flat board 3, entablature 14, bottom end rail 15, two first stands 1, two second stands 8 mutually support and form the region that is used for holding airfoil 18. Can seal the region that holds airfoil 18 through setting up entablature 14 and bottom end rail 15 for airfoil 18 is more firm fixes between two bearings 5, and then makes measured data more accurate, and through setting up entablature 14 and bottom end rail 15, makes entablature 14, bottom end rail 15, first stand 1 mutually support with second stand 8, and the device is compacter, complete, and convenient the removal ensures measuring result's accuracy.
The lower part of the lower beam 15 is also fixedly connected with a base 16, a level gauge is installed on the base 16, and the base 16 is used for supporting the whole device and is conveniently placed in a wind tunnel. Through setting up base 16 and installing the spirit level on base 16, conveniently adjust the horizontality of whole device to and conveniently place this device.
The spring of the invention is a special spring, and the elastic modulus is designed as follows: under maximum negative or positive lift conditions of the airfoil 18, the displacement up and down the model is within the proper range; the motor 17 is selected according to the following criteria: the holding torque of the motor 17 can enable the wing profile 18 to freely adjust the angle under the conditions of maximum wind speed and maximum torque; the scale 12 and the spring are calibrated beforehand.
The invention also discloses a method for measuring the wing profile lifting force by using the device, which comprises the following steps:
two suitable end plates 19 are selected to be sleeved at two ends of the wing section 18, so that the end plates 19 generate two-dimensional flow on the wing section 18,
the two ends of the wing profile 18 are respectively fixed between the two bearings 5,
the device for measuring the airfoil lift is placed in a wind tunnel,
the displacement value of the read pointer 13 up or down,
the motor 17 is started, the attack angle of the wing profile 18 is changed,
the displacement value of the pointer 13 upwards or downwards is read again until the measurement is finished.
The use method of the device comprises the following steps:
the whole device is fixed in a wind tunnel, and before an experiment begins, two proper end plates 19 are selected to be sleeved at two ends of the wing section 18, so that the end plates 19 generate two-dimensional flow on the wing section 18; the wing profile 18 is fixed on the bearing 5 between the upper spring 6 and the lower spring 7 and is kept still, while the pointer 13 points to a scale, and this time is the weight of the wing profile 18. After the experiment is started, namely the wind tunnel starts to operate, the wing profile 18 drives the bearing 5 to compress the upper spring 6 or the lower spring 7 due to the upward or downward lifting force applied to the wing profile 18, the pointer 13 is driven to move, and the lifting force of the wing profile 18 is obtained according to the force value on the pointer 13 indicator scale 12.
Claims (9)
1. A device for measuring airfoil lift for placement in a wind tunnel, comprising:
two first upright posts (1) are oppositely and vertically arranged,
two upper flat plates (2) which are horizontally arranged and respectively fixed at the upper ends of the corresponding first upright posts (1),
two lower flat plates (3) which are horizontally arranged and respectively fixed at the lower ends of the corresponding first upright posts (1),
two linear guide rails (4) which are vertically and oppositely arranged, two ends of each linear guide rail are respectively fixed on the corresponding upper flat plate (2) and the corresponding lower flat plate (3),
the two bearings (5) are oppositely arranged and are respectively sleeved on the two linear guide rails (4), the two bearings (5) are respectively used for fixing two ends of the wing section (18), so that the wing section (18) is horizontally fixed between the two bearings (5),
two upper springs (6) are respectively sleeved on the upper half part of the linear guide rail (4), the upper ends of the upper springs are fixed, the lower ends of the upper springs are propped against the upper ends of the corresponding side bearings (5),
two lower springs (7) are respectively sleeved on the lower half parts of the linear guide rails (4), the lower ends of the lower springs are fixed, the upper ends of the lower springs are propped against the lower ends of the corresponding side bearings (5),
the two bearings (5) are also used for the wing profile (18) to drive the bearings (5) to move upwards or downwards along the linear guide rail (4) after the wing profile (18) is subjected to the upwards or downwards lifting force in the wind tunnel, so that the upwards or downwards displacement value of the wing profile (18) is measured, and the lifting force of the wing profile (18) is obtained.
2. The device for measuring the wing-shaped lift force according to claim 1, further comprising two second upright columns (8) which are arranged oppositely and vertically, wherein one end of each of the two upper flat plates (2) is fixedly connected with the upper end of the first upright column (1), the other end of each of the two upper flat plates is fixedly connected with the upper end of the corresponding second upright column (8), one end of each of the two lower flat plates (3) is fixedly connected with the lower end of the first upright column (1), the other end of each of the two lower flat plates is fixedly connected with the lower end of the corresponding second upright column (8), the two first upright columns (1), the two second upright columns (8), the two upper flat plates (2) and the two lower flat plates (3) are matched with each other to form two opposite frame-shaped areas, and the two frame-shaped areas are used for accommodating the linear guide rails (4), a bearing (5), an upper spring (6) and a lower spring (7).
3. The device for measuring the wing-shaped lift force according to claim 2, characterized in that an upper support plate (9) and a lower support plate (10) are fixedly connected between the first upright (1) and the second upright (8) in the same frame-shaped region, two ends of the two upper support plates (9) and the two lower support plates (10) are fixedly connected with the inner sides of the corresponding first upright (1) and the corresponding second upright (8), respectively, the two upper support plates (9) and the two lower support plates (10) are arranged in parallel with the upper flat plate (2), two ends of the two linear guide rails (4) are fixed on the corresponding upper support plates (9) and the corresponding lower support plates (10), and the first upright (1), the second upright (8), the upper support plates (9) and the lower support plates (10) in the same frame-shaped region are mutually matched to form a containing space for containing the linear guide rails (4), A bearing (5), an upper spring (6) and a lower spring (7).
4. A device for measuring the lift of a wing profile according to any one of claims 1-3, characterised in that a motor (17) is also fixedly connected to one of said bearings (5), that the output shaft of said motor (17) is journalled in the shaft of the wing profile (18), and that said motor (17) is adapted to rotate the wing profile (18) via the shaft of the wing profile (18) and thereby to change the angle of attack of the wing profile (18).
5. A device for measuring the lift of a wing profile according to claim 4, characterised in that the other bearing (5) is arranged to fix one end of the wing profile (18) by means of a fixing element (11), said fixing element (11) being fixedly connected to the respective bearing (5), said fixing element (11) cooperating with the motor (17) for fixing the wing profile (18) by means of the shaft of the fixed wing profile (18).
6. The device for measuring the airfoil lift force according to claim 5, characterized in that a scale (12) is adhered to any one of the two first columns (1) or the two second columns (8) from top to bottom, a horizontally arranged pointer (13) is fixedly connected to any one of the bearings (5), the pointer (13) and the scale (12) are arranged oppositely, the pointer (13) is used for marking the displacement value of the bearing (5) upwards or downwards, and the lift force of the airfoil (18) is obtained by reading the value.
7. A device for measuring airfoil lift according to claim 6, characterized in that an upper cross beam (14) is fixedly connected between the two upper plates (2) and a lower cross beam (15) is fixedly connected between the two lower plates (3), and the upper cross beam (14), the lower cross beam (15), the two first uprights (1) and the two second uprights (8) cooperate with each other to form a region for accommodating an airfoil (18).
8. The device for measuring the wing lift according to claim 7, characterized in that a base (16) is fixedly connected below the lower cross beam (15), a level gauge is installed on the base (16), and the base (16) is used for supporting the whole device and is conveniently placed in the wind tunnel.
9. A method for measuring the lift of an airfoil based on the device of claims 1-8, characterized by the steps consisting of:
two proper end plates (19) are selected to be sleeved at the two ends of the wing profile (18), so that the end plates (19) generate two-dimensional flow on the wing profile (18),
the two ends of the wing profile (18) are respectively fixed between the two bearings (5),
the device for measuring the airfoil lift is placed in a wind tunnel,
reading the displacement value of the pointer (13) upwards or downwards,
the motor (17) is started to change the attack angle of the wing profile (18),
and reading the displacement value of the pointer (13) upwards or downwards again until the measurement is finished.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010962467.XA CN112161776A (en) | 2020-09-14 | 2020-09-14 | Device and method for measuring airfoil lift force |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010962467.XA CN112161776A (en) | 2020-09-14 | 2020-09-14 | Device and method for measuring airfoil lift force |
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| CN112161776A true CN112161776A (en) | 2021-01-01 |
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| CN202010962467.XA Pending CN112161776A (en) | 2020-09-14 | 2020-09-14 | Device and method for measuring airfoil lift force |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112924132A (en) * | 2021-01-29 | 2021-06-08 | 同济大学 | Vertical torsion two-degree-of-freedom segment model wind tunnel test system |
| CN112924714A (en) * | 2021-02-19 | 2021-06-08 | 浪潮电子信息产业股份有限公司 | Wind speed measuring device and server |
| CN113815513A (en) * | 2021-10-29 | 2021-12-21 | 北京航空航天大学 | Aerodynamic coupling test system for paddle wing of vehicle-mounted variable incidence angle aircraft |
| CN114608783A (en) * | 2022-03-11 | 2022-06-10 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling airfoil |
| CN115597823A (en) * | 2022-09-08 | 2023-01-13 | 成都流体动力创新中心（Cn） | Open wind tunnel unmanned aerial vehicle wing type aerodynamic force measurement system and method |
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2020
- 2020-09-14 CN CN202010962467.XA patent/CN112161776A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112924132A (en) * | 2021-01-29 | 2021-06-08 | 同济大学 | Vertical torsion two-degree-of-freedom segment model wind tunnel test system |
| CN112924132B (en) * | 2021-01-29 | 2022-02-18 | 同济大学 | Vertical torsion two-degree-of-freedom segment model wind tunnel test system |
| CN112924714A (en) * | 2021-02-19 | 2021-06-08 | 浪潮电子信息产业股份有限公司 | Wind speed measuring device and server |
| CN112924714B (en) * | 2021-02-19 | 2023-02-24 | 浪潮电子信息产业股份有限公司 | Wind speed measuring device and server |
| CN113815513A (en) * | 2021-10-29 | 2021-12-21 | 北京航空航天大学 | Aerodynamic coupling test system for paddle wing of vehicle-mounted variable incidence angle aircraft |
| CN114608783A (en) * | 2022-03-11 | 2022-06-10 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling airfoil |
| CN114608783B (en) * | 2022-03-11 | 2024-01-09 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling wing section |
| CN115597823A (en) * | 2022-09-08 | 2023-01-13 | 成都流体动力创新中心（Cn） | Open wind tunnel unmanned aerial vehicle wing type aerodynamic force measurement system and method |
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