CN111696412A - Experiment and simulation demonstration device for wing lift force and surface flow - Google Patents
Experiment and simulation demonstration device for wing lift force and surface flow Download PDFInfo
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- CN111696412A CN111696412A CN202010719866.3A CN202010719866A CN111696412A CN 111696412 A CN111696412 A CN 111696412A CN 202010719866 A CN202010719866 A CN 202010719866A CN 111696412 A CN111696412 A CN 111696412A
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B23/00—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes
- G09B23/06—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics
- G09B23/08—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics for statics or dynamics
- G09B23/12—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics for statics or dynamics of liquids or gases
Abstract
The invention discloses an experimental and simulation demonstration device for wing lift force and surface flow, which comprises: the device comprises a wing model, a supporting mechanism, a hose, a multi-pipe pressure meter, colored smoke, a power device, a quick connector and a nut. The multi-tube pressure gauge in the experimental and simulation demonstration device can intuitively show the pressure difference between the upper surface pressure and the lower surface pressure of the measured wing model and the atmospheric pressure, so that the wing lift principle experiment and classroom simulation demonstration are carried out, the attack angle of the wing model is continuously increased through the supporting mechanism, the colored smoke flow display technology is combined, the airplane stall experiment and classroom simulation demonstration can be carried out, the theory and practice are combined, and the experimental and teaching effects are greatly improved. The device also has the advantages of convenient measurement and observation, easy processing, low cost, convenient assembly, simple experimental operation, good portability and the like.
Description
Technical Field
The invention belongs to the field of fluid mechanics experiments and teaching, relates to an important means of fluid mechanics research and teaching, namely experiment and simulation demonstration, and particularly relates to a fluid mechanics experiment and simulation demonstration device.
Background
Fluid experiments generally include flow display and flow measurement. The flow display mainly aims at visualizing the flow process, the flow measurement mainly aims at acquiring quantitative information of the flow process, the flow display and the flow measurement complement each other and are a component part of experimental hydrodynamics, and through various flow display and measurement experiments, people can know complex flow phenomena, explore physical mechanisms and motion rules and provide scientific basis for establishing new concepts and mathematical models. The simulation demonstration is an important teaching means for enhancing the intuitive and perceptual knowledge of the trainees. The simulation demonstration is to vividly demonstrate some real objects, and for objective reasons, flight students can not move some parts of the plane into the classroom in classroom teaching, and independent experimental teaching or observation is difficult to guarantee in time or effect, and the simulation demonstration can combine classroom teaching instant teaching with some important devices, concepts and definitions. Meanwhile, each theoretical breakthrough in the fluid mechanics development process and the application thereof in engineering almost begin from experiments and observation on the flow phenomenon. For example, the reynolds transition experiment in 1880, the mach shock wave phenomenon experiment in 1888, the concept of the boundary layer proposed in prandtl in 1904, the von karman analysis on the circular vortex street of the cylinder in 1912 and the like are not based on experiments and demonstration. Aircraft lift is critical to aircraft performance, and the importance of aircraft lift is more laterally evidenced by the statement "strive to reduce one gram of aircraft weight" in the aviation world. The aircraft lift force is mainly generated by the wings, and the principle of the lift force generation can be explained by Bernoulli's theorem, but the pure theoretical explanation is too abstract and not easy to understand. Aircraft stall, which is extremely dangerous to pilots due to flow separation caused by an excessive angle of attack, causes a sharp drop in aircraft lift. It is necessary to design a set of devices to reproduce these complex physical concepts and phenomena, which not only can enhance the practical ability of flight trainees, but also can deepen the trainees' understanding of these important concepts. Meanwhile, in the traditional classroom teaching, students see formula derivation and flowing photos, and possibly have partial videos for helping understanding, and the concepts are still abstract to flight students and difficult to have intuitive understanding. On-site teaching is limited in time and poor in theoretical effect.
Therefore, the design of the experimental and simulation demonstration device which is feasible, convenient and easy to use and good in experimental and demonstration effects and methods has important significance.
Disclosure of Invention
The invention aims to provide an experimental and simulation demonstration device for wing lift force and surface flow, and the innovation points of the invention are as follows: the upper surface and the lower surface of the wing profile can be separated, so that the installation and the connection of the hose are greatly facilitated, and the cost is greatly reduced; secondly, the device combines quantitative measurement, utilizes the flow to show stall principle and phenomenon for flight student well. The device not only is applicable to fields such as experimental study, classroom demonstration teaching, also has the practical value of reference, reference to popular science teaching moreover.
In order to design a set of well-designed device, reproduce some physical concepts and phenomena which are very important for flight students and solve the problems existing in the traditional classroom teaching and on-site teaching of the flight students, the invention provides an experimental and simulation demonstration device for wing lift force and surface flow, which comprises: the device comprises a wing model, a supporting mechanism, a hose, a multi-pipe pressure meter, colored smoke, a power device, a quick connector and a screw cap. The wing model is hollow and detachable, the wing model is fixed on the supporting mechanism, pressure measuring holes are respectively formed in the central line positions of the upper surface and the lower surface of the wing model, the inner wall of each pressure measuring hole is tapped and connected with the quick connector, the hose is screwed and sealed by the nut and is led out to be connected with the multi-pipe pressure gauge, the power device is placed at a certain distance from the front edge of the wing model, and colored smoke is distributed at the outlet of the power device.
Preferably, in order to enable the experiment and simulation demonstration device to be easy to obtain and process and solve the problem that the hose is difficult to install and replace in the past, the wing model adopts an upper wing surface and a lower wing surface which are in a hollow separation type, and the mode can be used for greatly facilitating multiple works such as installation, replacement and inspection of components such as quick connectors and hoses, and the whole set of device is low in cost and convenient to install and debug.
Preferably, the connection mode of the upper wing surface and the lower wing surface of the wing model is in a fixed or movable mode, the wing model can be used for one time, the wing model can be glued conveniently and quickly, the wing model can be repeatedly used and connected through movable bolts, and the processing complexity is slightly increased, but the wing model can be repeatedly used to reduce the cost.
Preferably, the machining material of the wing model is acrylic, and the material is easy to obtain, low in cost, easy to machine and form, light in weight and easy to carry.
Preferably, the corresponding positions of the upper and lower wing surfaces of the wing model are provided with the same number of pressure measurement holes, the corresponding positions are provided with holes to ensure the comparison effectiveness of test data, the upper and lower positions are the same number to ensure the effectiveness of the data and reduce various error sources such as accidental errors and system errors.
Preferably, pressure measurement holes of the upper wing surface and the lower wing surface of the wing model are connected with the quick connector through threads, the threads are sealed or are matched with a sealing ring through common threads, so that the sealing effect of the joint of the parts can be fully guaranteed, and the device has obvious effects on improving the experimental and simulation precision of the device and the reliability of data and reducing errors.
Preferably, the angle and the height of the wing model supporting mechanism are adjustable, the wing attack angle can be continuously adjusted after the wing model is fixed on the supporting mechanism, and different attack angle lift coefficient curve drawing experiments can be performed through certain improvement. By the supporting mechanism, on one hand, the installation height of the wing model can be adjusted, and the adjustment of the distance between the wing model and the bottom surface of the supporting mechanism is realized, so that the wing chord height of the wing model is adapted to the height of the air outlet of the wind speed generating device; on the other hand, the included angle between the wing chord of the wing model and the bottom surface of the supporting mechanism can be adjusted, so that the included angle between the wing chord of the wing model and the axis of the air outlet of the wind speed generating device is changed, and the experiment and the simulation demonstration of the wing chord and the incoming flow when the included angle exists on the horizontal plane (namely sideslip) are carried out, so that the cognition and understanding of students on related knowledge are further deepened.
Preferably, the wind speed generating device is a speed-adjustable wind speed generating device. Through adjustment, the wind speed generating device can generate different wind speeds, so that the display of the multi-tube pressure gauge is changed, and the knowledge and understanding of students on relevant knowledge are deepened.
Preferably, the wind speed generating device is an axial flow fan or a centrifugal fan, and a small or miniature axial flow fan or a small miniature centrifugal fan can be adopted during simulation demonstration, so that on one hand, the cost can be effectively reduced, and in addition, the portability when the wind speed generating device is used as demonstration equipment or a teaching aid is also considered. And when carrying out large-scale experiment, then consider to use the frequency conversion fan in order to obtain better effect.
Preferably, when one end of the quick connector is screwed into the wing model, the surface of the quick connector is level with the outer surface of the wing model, and therefore the problem that the experiment and demonstration results are inaccurate due to interference on airflow on the surface of the wing model is avoided. The hoses are equal in length, so that the same flow resistance in the pipelines is ensured, and experimental and demonstration errors caused by different lengths are avoided.
According to the experimental and simulation demonstration device for the wing lift force and the surface flow, the pressure difference between the upper surface pressure and the lower surface pressure of the measured wing model and the atmospheric pressure can be intuitively displayed by the multi-tube pressure gauge in the experimental and simulation demonstration device, so that the wing lift force principle experiment and the classroom simulation demonstration are performed, the attack angle of the wing model is continuously increased through the supporting mechanism, the colored smoke flow display technology is combined, the airplane stall experiment and the classroom simulation demonstration can be performed, the theory and practice are combined, and the experimental and teaching effects are greatly improved. This experiment and simulation presentation device can be fine carry on experiments and simulation demonstration such as wing lift, stall, have moreover that measurement, observation are convenient, the device workable, with low costs, the equipment of being convenient for, experiment easy operation, advantages such as portability are good, can be fine satisfy experiment and teaching demand.
Drawings
Fig. 1 is a schematic composition diagram of an experimental and simulated demonstration device for wing lift and surface flow.
Detailed Description
The following describes the embodiments of the present invention with reference to the accompanying drawings.
Example 1
An experimental and simulation demonstration device for wing lift and surface flow, as shown in fig. 1, specifically comprises: wing model 1, supporting mechanism 2, hose 3, multitube pressure gauge 4, colored smog 5, power device 6, quick-operation joint 7, nut 8, wherein wing model 1 is fixed in on supporting mechanism 2, the tapping of wing model surface pressure survey hole inner wall, the tapping type is sealed screw thread, the internal thread is connected with quick-operation joint 7, 8 evenly arrange schemes are adopted in wing model upper and lower surface pressure hole in this embodiment, hose 3 is connected with quick-operation joint 7, utilize nut 8 to screw up sealed, and draw out and link to each other with multitube pressure gauge 4, hose length is the same, power device 6 places in wing model 1 leading edge certain distance department.
During experiment or simulation demonstration, the height of the model supporting mechanism can be fixed, and the experiment and demonstration of the wing lift principle are carried out through the change of the wing model within a smaller attack angle range (not exceeding the stalling attack angle).
Example 2
The experimental and simulation demonstration device for the wing lift force and the surface flow in the embodiment has the same structure as that in the embodiment 1, and is mainly characterized in that the included angle between the wing chord of the wing model and the central line of the power device outlet on the horizontal plane is not zero, and the wing sideslips.
During experiment or simulation demonstration, the wing lift force experiment and simulation demonstration under different sideslip angles are carried out by adjusting the inclination angle of the supporting mechanism, namely the included angle between the wing chord of the wing model and the central line of the power device outlet in the horizontal plane.
Example 3
The experimental and simulation demonstration device for the wing lift force and the surface flow in the embodiment has the structure basically the same as that of the embodiment 2, and mainly has the following differences: (1) the inclination angle of the supporting mechanism 2 is zero, and the wings do not sideslip; (2) the angle of attack of the wing model is large (super stall angle of attack); (3) colored smoke is distributed at the outlet of the power device 6.
During experiment or simulation demonstration, the attack angle of the wing model is adjusted to a larger attack angle through the supporting mechanism, colored smoke is distributed at the outlet of the power device at the moment, and flow display and the multi-pipe pressure gauge are combined to perform stall experiment and simulation demonstration, so that the cognition and understanding of a student on a stall phenomenon are deepened.
Finally, it should be noted that the above-mentioned embodiments are only preferred embodiments of the present invention, and not intended to limit the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and equivalents can be made in the technical solutions described in the foregoing embodiments, or some technical features thereof can be replaced. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An experimental and simulated demonstration device for wing lift and surface flow, comprising: wing model (1), supporting mechanism (2), hose (3), multitube pressure gauge (4), coloured smog (5), power device (6), quick-operation joint (7), nut (8), on wing model (1) was fixed in supporting mechanism (2), surface center line position opened respectively about wing model (1) had a plurality of pressure measuring holes, and the pressure measuring hole is connected with quick-operation joint (7), sheathes in nut (8) fastening and sealed hose (3) and quick-operation joint (7) junction, and hose (3) are drawn forth and are linked to each other with multitube pressure gauge (4), and power device (6) are placed in wing model (1) leading edge certain distance department, and coloured smog (5) are laid in power device (6) exit position.
2. The experimental and simulation demonstration device for the lift force and the surface flow of the wings as claimed in claim 1, wherein the upper and lower wing surfaces of the wing model (1) are hollow and separated.
3. The experimental and simulation demonstration device for the lift force and the surface flow of the wings as claimed in claim 2, wherein the upper and lower wing surfaces of the wing model (1) can be connected in a fixed or movable manner.
4. The experimental and simulation demonstration device for wing lift and surface flow according to any one of claims 1 to 3, wherein the wing model (1) is made of acrylic.
5. The experimental and simulation demonstration device for the lift force and the surface flow of the wings as claimed in any one of claims 1 to 3, wherein the corresponding positions of the upper and lower wing surfaces of the wing model (1) are respectively provided with an equal number of pressure measurement holes.
6. The experimental and simulation demonstration device for the lift force and the surface flow of the wings as claimed in claim 5, wherein the pressure measuring holes of the upper and lower wing surfaces of the wing model (1) are connected with the quick connectors (7) through threads.
7. The experimental and simulated demonstration device for lift and surface flow of airfoils according to claim 1 wherein said supporting means (2) is height adjustable and the angle of the pedestal portion is adjustable.
8. The experimental and simulated demonstration device for the lift and surface flow of an airfoil according to claim 1 characterised in that said power means (6) is an adjustable wind speed device.
9. The experimental and simulation demonstration device for airfoil lift and surface flow according to claim 1 or 8 wherein the power device is an axial flow or centrifugal fan.
10. The experimental and simulation demonstration device for wing lift and surface flow according to claim 1, wherein after the quick connector is connected with the airfoil surface, the airfoil model surface has no protrusion or depression, and the lengths of the hoses are the same.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010719866.3A CN111696412A (en) | 2020-07-23 | 2020-07-23 | Experiment and simulation demonstration device for wing lift force and surface flow |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010719866.3A CN111696412A (en) | 2020-07-23 | 2020-07-23 | Experiment and simulation demonstration device for wing lift force and surface flow |
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| CN111696412A true CN111696412A (en) | 2020-09-22 |
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| CN202010719866.3A Pending CN111696412A (en) | 2020-07-23 | 2020-07-23 | Experiment and simulation demonstration device for wing lift force and surface flow |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116183157A (en) * | 2023-04-25 | 2023-05-30 | 太原理工大学 | Intelligent wind tunnel experimental device |
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2020
- 2020-07-23 CN CN202010719866.3A patent/CN111696412A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116183157A (en) * | 2023-04-25 | 2023-05-30 | 太原理工大学 | Intelligent wind tunnel experimental device |
| CN116183157B (en) * | 2023-04-25 | 2023-07-11 | 太原理工大学 | Intelligent wind tunnel experimental device |
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