CN111579203A - Two-dimensional airfoil pressure measurement system - Google Patents
Two-dimensional airfoil pressure measurement system Download PDFInfo
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
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Abstract
The invention relates to a two-dimensional airfoil pressure measurement system. The system comprises: the device comprises a dynamic adjusting mechanism, an air conduit, a pressure sensor, a data acquisition card and a computer; the two-dimensional airfoil model to be measured is vertically fixed in a dynamic adjusting mechanism, and the dynamic adjusting mechanism is used for adjusting the translation parameters and the rotation parameters of the two-dimensional airfoil model in the horizontal direction according to signals output by a computer; the first end of the air duct is connected with a cavity in the two-dimensional airfoil model, and the second end of the air duct extends out of the two-dimensional airfoil model to be communicated with the atmosphere; the pressure sensor is fixed on the two-dimensional airfoil model; the data acquisition end of the data acquisition card is connected with a signal line of the pressure sensor, and the data output end of the data acquisition card is connected with the computer; and the computer is used for obtaining a pressure measurement result of the two-dimensional airfoil model according to the pressure data acquired by the data acquisition card. The invention can improve the pressure measurement accuracy and reduce the complexity of the measurement process.
Description
Technical Field
The invention relates to the field of helicopter aerodynamics, in particular to a two-dimensional airfoil pressure measuring system.
Background
The rotor wing is a key part of the helicopter, can provide lift force, thrust force and moment required by maneuvering flight for the helicopter, and the analysis of the dynamic pressure on the surface of the rotor wing is the core problem of the aerodynamics of the helicopter.
Two-dimensional airfoil surface pressure measurement in wind tunnel is one of the main means of studying rotor aerodynamic problem, however the pressure measuring device that current experimental apparatus adopted mainly utilizes the pitot tube, when using the pitot tube to measure pressure, has following shortcoming: (1) the pitot tube per se can generate disturbance to a flow field, so that the measurement precision is reduced, and the error is more obvious when the dynamic pressure is measured. (2) When the pitot tube is used for experiments, theoretically, air in the pitot tube and the rubber tube must be completely exhausted, then the lower end of the pitot tube is placed in water flow, and an inlet of the total pressure tube is opposite to the flow velocity direction of a measuring point. However, in practical application, the bubbles are not easy to be discharged completely, once the lower end of the air bubble is separated from the water surface, the air bubble needs to be discharged again after entering, and the process is complicated. In addition, the direction of the flow velocity at the point of measurement is not easily achieved.
Disclosure of Invention
The invention aims to provide a two-dimensional airfoil pressure measurement system, which is used for improving the pressure measurement accuracy and reducing the complexity of the measurement process.
In order to achieve the purpose, the invention provides the following scheme:
a two-dimensional airfoil pressure measurement system comprising: the device comprises a dynamic adjusting mechanism, an air conduit, a pressure sensor, a data acquisition card and a computer;
the dynamic adjusting mechanism is used for adjusting the translation parameters and rotation parameters of the two-dimensional airfoil model in the horizontal direction according to signals output by the computer; the first end of the air guide pipe is connected with a cavity, the cavity is arranged in the two-dimensional airfoil model, and the second end of the air guide pipe extends out of the two-dimensional airfoil model to be communicated with the atmosphere; the pressure sensor is fixed on the two-dimensional airfoil model; the data acquisition end of the data acquisition card is connected with the signal line of the pressure sensor, and the data output end of the data acquisition card is connected with the computer; and the computer is used for obtaining a pressure measurement result of the two-dimensional airfoil model according to the pressure data acquired by the data acquisition card.
Optionally, the dynamic adjustment mechanism includes a bracket, a rotating shaft, a first motor, a transmission mechanism, a second motor and a speed reducer;
the 1/4 chord line position of the two-dimensional airfoil model is penetrated by a rotating shaft, and the rotating shaft is fixedly connected with the two-dimensional airfoil model; the upper end part of the rotating shaft is fixed at the upper end of the bracket;
an output shaft of the first motor is connected with a first end of the transmission mechanism, and a second end of the transmission mechanism is connected with the lower end of the rotating shaft; the transmission mechanism is used for driving the two-dimensional airfoil model to translate in the horizontal direction according to the rotation of the first motor;
an output shaft of the second motor is connected with an input shaft of the speed reducer, and an output shaft of the speed reducer is connected with the lower end of the rotating shaft;
and the signal output end of the computer is connected with the control end of the first motor and the control end of the second motor.
Optionally, the transmission mechanism adopts a worm gear mechanism, a worm wheel of the worm gear mechanism is connected with an output shaft of the first motor, and a worm of the worm gear mechanism is connected with the lower end of the rotating shaft.
Optionally, the second end of the transmission mechanism is connected with the lower end of the rotating shaft through a sliding block, the second motor and the speed reducer; the second end of the transmission mechanism is fixedly connected with the sliding block, the second motor is fixedly connected with the sliding block, the sliding block is sleeved on the guide rail of the support, and the sliding block can slide on the guide rail.
Optionally, the number of the pressure sensors is multiple; the pressure sensors are vertically fixed in mounting holes on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor is vertical to the surface of the two-dimensional airfoil model; the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes perpendicular to the surface of the two-dimensional airfoil model;
and the reference pressure end of the pressure sensor is connected to the cavity through a reference pressure conduit, the cavity is connected with the first end of the air conduit, and the second end of the air conduit is placed in the atmosphere outside the two-dimensional airfoil model.
Optionally, the two-dimensional airfoil model comprises a first end section, a middle section and a second end section, the first end section, the middle section and the second end section are sequentially fixed by pins, and the first end section, the middle section and the second end section are fixed in a span-wise direction by gluing; the pressure sensor, the reference pressure conduit, and the cavity are all located within the intermediate section.
Optionally, a first groove and a second groove are formed in the middle section;
the cavity is fixed in the first groove, part of the pipe section of the first end of the air conduit is positioned in the first groove, and part of the pipe section of the second end of the air conduit passes through the through hole in the first end section and extends to the outside of the two-dimensional airfoil model;
the reference pressure conduit is fixed in the second groove;
the second groove is communicated with the first groove; and a signal wire of each pressure sensor sequentially passes through the second groove, the first groove and a through hole in the second end section to extend to the outside of the two-dimensional airfoil model.
Optionally, the plurality of pressure sensors are divided into a first sensor group and a second sensor group, and the first sensor group and the second sensor group each include a plurality of pressure sensors;
the first sensor group is fixed in a mounting hole in the upper surface of the two-dimensional airfoil model, and the second sensor group is fixed in a mounting hole in the lower surface of the two-dimensional airfoil model; and the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are arranged in a staggered manner in the chord direction of the two-dimensional airfoil model.
Optionally, the model of the data acquisition card is NI9220, and the number of channels is 16.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the pressure sensor is arranged in the two-dimensional airfoil model, the device cannot influence a flow field, the measurement precision is high and can reach 0.03Pa, and the error is less than two thousandths. And the preparation in the earlier stage of measurement is simple and easy, just can install two-dimensional airfoil model on dynamic adjustment mechanism, need not other complicated operations, and the process is simple and easy, and measurement efficiency is high. In addition, the whole measuring system can be repeatedly tested after being installed once, does not need secondary debugging and has high repeatability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic structural view of a two-dimensional airfoil pressure measurement system of the present invention;
FIG. 2 is a schematic structural diagram of a dynamic adjustment mechanism according to the present invention;
FIG. 3 is a schematic view of the installation of the pressure sensor of the present invention;
fig. 4 is a three-dimensional schematic view of a pressure sensor of the present invention.
Number designation in the figures: 1-a dynamic adjusting mechanism, 2-a two-dimensional airfoil model, 3-an air conduit, 4-a data acquisition card, 5-a power supply, 6-a computer, 7-a bracket, 8-a first motor, 9-a transmission mechanism, 10-a guide rail, 11-a slide block, 12-a second motor, 13-a speed reducer, 14-a rotating shaft, 15-a closed cavity, 16-a pressure sensor, 17-a reference pressure conduit, 18-a signal line and 19-a cover plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
FIG. 1 is a schematic structural diagram of a two-dimensional airfoil pressure measurement system of the present invention. As shown in FIG. 1, the two-dimensional airfoil pressure measurement system of the present invention comprises: the device comprises a dynamic adjusting mechanism 1, an air conduit 3, a pressure sensor 16, a data acquisition card 4 and a computer 6.
The two-dimensional airfoil model 2 to be measured is vertically fixed in the dynamic adjusting mechanism 1, the control end of the dynamic adjusting mechanism 1 is connected with the signal output end of the computer 6, and the dynamic adjusting mechanism 1 is used for adjusting the translation parameters and the rotation parameters of the two-dimensional airfoil model 2 in the horizontal direction according to the signals output by the computer 6.
Fig. 2 is a schematic structural diagram of the dynamic adjustment mechanism of the present invention, and as shown in fig. 2, the dynamic adjustment mechanism 1 includes a bracket 7, a rotating shaft 14, a first motor 8, a transmission mechanism 9, a second motor 12, and a speed reducer 13. The 1/4 chord line position of the two-dimensional airfoil model 2 is penetrated by a rotating shaft 14, and the rotating shaft 14 is fixedly connected with the two-dimensional airfoil model 2; the upper end portion of the rotary shaft 14 is fixed to the upper end of the bracket. For example, the upper end of the rotating shaft 14 may be mounted on a slide block of a bracket beam through a bearing, and the bracket beam is a guide rail on which the upper end of the two-dimensional airfoil model 2 slides. By adopting the mode, on one hand, the upper end of the two-dimensional airfoil model 2 is fixed, and on the other hand, the upper end of the two-dimensional airfoil model 2 can slide.
In the invention, the output shaft of the first motor 8 is connected with the first end of the transmission mechanism 9, and the second end of the transmission mechanism 9 is connected with the lower end of the rotating shaft 14. The transmission mechanism 9 is used for driving the rotating shaft 14 according to the rotation of the first motor 8 so as to drive the two-dimensional airfoil model 2 to translate in the horizontal direction, so as to simulate the sinking and floating movement of the blade model. An output shaft of the second motor 12 is connected with an input shaft of the speed reducer 13, and an output shaft of the speed reducer 13 is connected with a lower end of the rotating shaft 14. The rotating speed of the second motor 12 is reduced through the speed reducer 13, and then the two-dimensional airfoil model 2 is driven to rotate in the horizontal direction, so that the pitching motion of the blade model is simulated. The signal output end of the computer 6 is connected with the control end of the first motor 8 and the control end of the second motor 12, and the computer 6 outputs control signals through the signal output end to control the motion rules of the first motor 8 and the second motor 12 respectively.
The second end of the transmission mechanism 9 may be directly connected to the lower end of the rotating shaft 14, or may be connected to the rotating shaft 14 through a second motor. As a specific example, as shown in fig. 2, the connection mode of the transmission structure 9 is as follows: the second end of the transmission mechanism 9 is fixedly connected with the sliding block 11, the second motor 12 is fixedly connected with the sliding block 11, and at this time, the second end of the transmission mechanism 9 is connected with the lower end of the rotating shaft 14 through the sliding block 11, the second motor 12 and the speed reducer 13. The sliding block 11 is sleeved on the guide rail 10 of the bracket, and the sliding block 11 can slide on the guide rail 10. By controlling the first motor 8 and the second motor 12, a static blowing experiment of the two-dimensional airfoil model 2 can be performed, and a sinking and floating movement experiment, a pitching movement experiment and a sinking and floating and pitching two-coupled movement experiment of the two-dimensional airfoil model 2 can be performed. During static blowing experiments, only the airfoil angle of attack and the incoming flow speed need to be changed, the airfoil angle of attack is adjusted through the first motor 12, the incoming flow wind speed is regulated and controlled through wind tunnel control software, and data of the pressure sensors at different angles of attack and different wind speeds are collected. During the dynamic blowing experiment, the following 6 adjustment parameters are provided: the wing profile moves according to the sine rule. During the experiment, the dynamic adjusting mechanism 1 is placed in a wind tunnel, the geometric front edge of the two-dimensional airfoil model 2 points to the incoming flow direction, and the forward blowing experiment can be carried out; the geometrical rear edge points to the incoming flow direction, and a reverse blowing experiment can be carried out. And then the pressure data acquired by the data acquisition card 4 is used for obtaining the pressure measurement data of the two-dimensional airfoil model 2 in the experimental process.
The specific structure of the transmission mechanism 9 is determined according to actual conditions, and the function of the transmission mechanism is to drive the two-dimensional airfoil model 2 to translate in the horizontal direction according to the output of the first motor 8. As a specific example, the transmission mechanism 9 may employ a worm gear mechanism. As shown in fig. 2, the worm gear mechanism includes a worm wheel connected to an output shaft of the first motor 8 and a worm fixed to a slider 11 fitted over the carriage rail 10. The rotation of the first motor 8 is converted into the translation of the sliding block 11 through the worm gear mechanism, so that the sliding block 11 arranged on the guide rail 10 makes horizontal translation to simulate the sinking and floating movement of the blade model.
According to the invention, the first end of the air duct 3 is connected with the cavity inside the two-dimensional airfoil model 2, and the second end of the air duct 3 extends out of the two-dimensional airfoil model 2 and is communicated with the atmosphere.
The pressure sensor of the present invention is fixed to the two-dimensional airfoil model 2. The data acquisition end of the data acquisition card 4 is connected with the signal line 18 of the pressure sensor, and the data output end of the data acquisition card 4 is connected with the computer 6. The data acquisition card 4 acquires pressure data of the pressure sensor, converts an analog signal of the pressure sensor into a digital signal and transmits the digital signal to the computer 6. The number of the pressure sensors is multiple, for example, 22, each pressure sensor is provided with two signal wires, one of the two signal wires is a signal data wire, the other one is a ground wire, the two signal wires are respectively connected to corresponding hole sites of the acquisition card, and each sensor is independently connected to one channel of the acquisition card. And the computer 6 is used for obtaining a pressure measurement result of the two-dimensional airfoil model 2 according to the pressure data acquired by the data acquisition card 4. The invention also comprises a power supply 5, wherein the power supply 5 is connected with the power supply end of the pressure sensor. The power supply 5 is a direct current power supply for supplying power to the pressure sensor. The pressure sensor is provided with two power lines, namely a positive 15V power line and a negative 15V power line, which are directly connected with the direct current power supply 5.
As a specific embodiment, the two-dimensional airfoil model 2 adopts an NACA0018 airfoil with the specification of 1000X 300. The purposes of selecting the wing profile mainly include two purposes: one is that the airfoil has small curvature and large thickness, the pressure sensor can be installed at the geometric rear edge as far as possible, and can be arranged more densely, so that more data can be measured, and the later experimental data processing interpolation is closer to the real situation; secondly, the wing profile is thicker, and more available space is arranged in the wing profile for arranging signal wires of the sensor. 22 mounting holes perpendicular to the model surface are dug at proper positions on the surface of the blade model so as to be convenient for mounting the pressure sensor and ensure that the pressure measuring surface is perpendicular to the model surface. Fig. 3 is a schematic view of the installation of the pressure sensor of the present invention. As shown in fig. 3, a plurality of pressure sensors are vertically fixed in mounting holes on the surface of the two-dimensional airfoil model 2, and the pressure measuring surface of each pressure sensor is perpendicular to the surface of the two-dimensional airfoil model 2; the surface of the two-dimensional airfoil model 2 is provided with a plurality of mounting holes vertical to the surface of the two-dimensional airfoil model 2; the reference pressure end of the pressure sensor is connected to the cavity 15 through a reference pressure conduit 17, the cavity 15 is connected with the first end of the air conduit 3, and the second end of the air conduit 3 is placed in the atmosphere outside the two-dimensional airfoil model 2.
The two-dimensional airfoil model 2 comprises a first end section, a middle section and a second end section, wherein the first end section, the middle section and the second end section are sequentially fixed through pins, and the first end section, the middle section and the second end section are fixed in a span-wise manner in a gluing mode; the pressure sensor, the reference pressure conduit 17 and the cavity 15 are all located within the intermediate section. The plurality of pressure sensors are divided into a first sensor group and a second sensor group, and the first sensor group and the second sensor group respectively comprise a plurality of pressure sensors; the first sensor group is fixed in a mounting hole on the upper surface of the two-dimensional airfoil model 2, and the second sensor group is fixed in a mounting hole on the lower surface of the two-dimensional airfoil model 2; and the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are arranged in the chord direction of the two-dimensional airfoil model 2 in a staggered manner.
Grooves are dug in the blade model, so that the signal wire 18 of the pressure sensor 16 and the reference pressure conduit 17 can be conveniently arranged. Specifically, a first groove and a second groove are formed in the middle section; the cavity 15 is fixed in the first groove, a part of the duct section at the first end of the air duct 3 is positioned in the first groove, and a part of the duct section at the second end of the air duct 3 extends to the outside of the two-dimensional airfoil model 2 through a through hole in the first end section; the reference pressure conduit 17 is fixed in the second groove; the second groove is communicated with the first groove; and the signal lines 18 of all the pressure sensors sequentially pass through the second groove, the first groove and the through hole in the second end section to extend to the outside of the two-dimensional airfoil model 2. The ABS plastic is used as the model material, and has higher strength and rigidity and smaller mass compared with other materials.
As an example, the pressure sensor 16 of the present invention may be a miniature dynamic pressure sensor, such as an HTP504 miniature dynamic pressure sensor with a frequency of up to 3KHz, as shown in FIG. 4, which is a three-dimensional schematic diagram of the pressure sensor of the present invention. The miniature dynamic pressure sensor is small in size, light in weight, 0-2 Kpa in measuring range and less than two thousandths of error range. And the miniature dynamic pressure sensor can be arranged in the model in a way of being vertical to the surface of the airfoil profile, and can be used for static pressure measurement and dynamic pressure measurement.
As a specific embodiment, the data acquisition card 4 of the present invention may adopt an NI9220 data acquisition card, the resolution of the data acquisition card is 16 bits, the data acquisition card is matched with the micro dynamic pressure sensor, the measurement precision can reach 0.03Pa, the number of channels is 16 channels, the sampling rate can reach 100kS/s/ch, and the data of 3.2MB/s can be generated at the maximum sampling rate. When 22 sensors are adopted in the invention, 32 channels can be adopted by two data acquisition cards 4 to acquire the data of the 22 sensors.
The computer is loaded with data acquisition software and a data processing program. And the data acquisition software is compiled based on Labview language, filters out the acquired high-frequency disordered signals through filtering processing, and only keeps relatively stable signals. The software has the following four advantages: clearing data; secondly, the storage of the real-time data designated file can be realized; the friendly visual interface can conveniently acquire data during experiments; and fourthly, displaying the real-time data of different airfoil surfaces in frames, and conveniently observing the experimental state. And a data processing program is compiled based on matlab software, and measured experimental data are interpolated by an integral method and a least square method to obtain the change curves of the airfoil normal force coefficient, the chord direction force coefficient, the lift coefficient, the resistance coefficient and the 1/4 chord line moment coefficient along with the attack angle.
The invention has the following advantages:
the pressure sensor is installed inside the two-dimensional airfoil profile model, the two-dimensional airfoil profile pressure measurement system cannot influence a flow field, the measurement precision is high and can reach 0.03Pa, and the error is less than two thousandths. The sampling rate of the miniature dynamic pressure sensor is as high as 3KHz, and the collected dynamic pressure value can reflect the real situation. The preparation is simple and easy in the earlier stage of the experiment, and the model is installed on the dynamic adjusting mechanism without other complex operations, so that the experiment efficiency is high. The two-dimensional airfoil pressure measurement system can be repeatedly tested after being once installed, secondary debugging is not needed, and repeatability is high.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (10)
1. A two-dimensional airfoil pressure measurement system, comprising: the device comprises a dynamic adjusting mechanism, an air conduit, a pressure sensor, a data acquisition card and a computer;
the dynamic adjusting mechanism is used for adjusting the translation parameters and rotation parameters of the two-dimensional airfoil model in the horizontal direction according to signals output by the computer; the first end of the air guide pipe is connected with a cavity, the cavity is arranged in the two-dimensional airfoil model, and the second end of the air guide pipe extends out of the two-dimensional airfoil model to be communicated with the atmosphere; the pressure sensor is fixed on the two-dimensional airfoil model; the data acquisition end of the data acquisition card is connected with the signal line of the pressure sensor, and the data output end of the data acquisition card is connected with the computer; and the computer is used for obtaining a pressure measurement result of the two-dimensional airfoil model according to the pressure data acquired by the data acquisition card.
2. The two-dimensional airfoil pressure measurement system of claim 1, wherein the dynamic adjustment mechanism comprises a bracket, a rotating shaft, a first motor, a transmission mechanism, a second motor, and a speed reducer;
the 1/4 chord line position of the two-dimensional airfoil model is penetrated by a rotating shaft, and the rotating shaft is fixedly connected with the two-dimensional airfoil model; the upper end part of the rotating shaft is fixed at the upper end of the bracket;
an output shaft of the first motor is connected with a first end of the transmission mechanism, and a second end of the transmission mechanism is connected with the lower end of the rotating shaft; the transmission mechanism is used for driving the two-dimensional airfoil model to translate in the horizontal direction according to the rotation of the first motor;
an output shaft of the second motor is connected with an input shaft of the speed reducer, and an output shaft of the speed reducer is connected with the lower end of the rotating shaft;
and the signal output end of the computer is connected with the control end of the first motor and the control end of the second motor.
3. The two-dimensional airfoil pressure measuring system according to claim 2, wherein the transmission mechanism is a worm gear mechanism, a worm wheel of the worm gear mechanism is connected with an output shaft of the first motor, and a worm of the worm gear mechanism is connected with a lower end of the rotating shaft.
4. The two-dimensional airfoil pressure measuring system of claim 2, wherein a second end of the transmission mechanism is connected to a lower end of the rotating shaft through a slider, the second motor and the reducer; the second end of the transmission mechanism is fixedly connected with the sliding block, the second motor is fixedly connected with the sliding block, the sliding block is sleeved on the guide rail of the support, and the sliding block can slide on the guide rail.
5. The two-dimensional airfoil pressure measurement system according to claim 1, wherein the pressure sensor is a miniature dynamic pressure sensor model HTP504, which is fixed inside the two-dimensional airfoil model in a manner perpendicular to the surface of the two-dimensional airfoil model.
6. The two-dimensional airfoil pressure measurement system of claim 5, wherein the number of said pressure sensors is plural; the pressure sensors are vertically fixed in mounting holes on the surface of the two-dimensional airfoil model, and the pressure measuring surface of each pressure sensor is vertical to the surface of the two-dimensional airfoil model; the surface of the two-dimensional airfoil model is provided with a plurality of mounting holes perpendicular to the surface of the two-dimensional airfoil model;
and the reference pressure end of the pressure sensor is connected to the cavity through a reference pressure conduit, the cavity is connected with the first end of the air conduit, and the second end of the air conduit is placed in the atmosphere outside the two-dimensional airfoil model.
7. The two-dimensional airfoil pressure measurement system according to claim 6, wherein the two-dimensional airfoil model comprises a first end section, a middle section and a second end section, the first end section, the middle section and the second end section are sequentially fixed by pins, and the first end section, the middle section and the second end section are fixed in a spanwise direction by gluing; the pressure sensor, the reference pressure conduit, and the cavity are all located within the intermediate section.
8. The two-dimensional airfoil pressure measurement system of claim 7, wherein a first groove and a second groove are formed in the middle section;
the cavity is fixed in the first groove, part of the pipe section of the first end of the air conduit is positioned in the first groove, and part of the pipe section of the second end of the air conduit passes through the through hole in the first end section and extends to the outside of the two-dimensional airfoil model;
the reference pressure conduit is fixed in the second groove;
the second groove is communicated with the first groove; and a signal wire of each pressure sensor sequentially passes through the second groove, the first groove and a through hole in the second end section to extend to the outside of the two-dimensional airfoil model.
9. The two-dimensional airfoil pressure measurement system of claim 6, wherein a plurality of said pressure sensors are divided into a first sensor group and a second sensor group, each of said first sensor group and said second sensor group including a plurality of said pressure sensors;
the first sensor group is fixed in a mounting hole in the upper surface of the two-dimensional airfoil model, and the second sensor group is fixed in a mounting hole in the lower surface of the two-dimensional airfoil model; and the pressure sensors of the first sensor group and the pressure sensors of the second sensor group are arranged in a staggered manner in the chord direction of the two-dimensional airfoil model.
10. The two-dimensional airfoil pressure measuring system according to claim 1, wherein the data acquisition card is of type NI9220 and has a channel number of 16.
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| CN112763179A (en) * | 2020-12-30 | 2021-05-07 | 吉林大学 | Wing type wind tunnel experiment bench |
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Application publication date: 20200825 |