CN106644361A - Simple method for measuring transonic wind tunnel test section space flow field symmetry - Google Patents
Simple method for measuring transonic wind tunnel test section space flow field symmetry Download PDFInfo
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a simple method for measuring transonic wind tunnel test section space flow field symmetry. Characteristics of large rigidity, stable pressure measurement and capability of bearing high Mach number tests of a conical cylinder model are used; a straight connection head and a rotary connection head are mounted on a wind tunnel attack angle mechanism, a ladder pressure measurement test for a number of groups of space symmetric attack angles are conducted, and local space flow field symmetry can be analyzed via pressure measurement data. According to the method, pressure measuring data of an outer side or inner side pressure measurement face of the conical cylinder model is processed in a space symmetric attack angle state during data processing operation, the pressure measuring data is converted into a Mach number and a pressure recovery coefficient, difference processing operation is performed, and local space flow field symmetry quality of a test section can be evaluated based on difference. Via use of the method, vehicle starting frequency can be effectively lowered, test cost can be reduced, and the local space flow field symmetry quality of the test section can be rapidly detected and analyzed.
Description
Technical field
The present invention relates to aerodynamic scope, especially experimental aerodynamics field, specially a kind of measurement is across sound
The symmetric simple and easy method in fast test chamber local space flow field.
Background technology
Wind-tunnel is the principle according to relative motion, and using movement air flow aircraft subscale test model realization flight simulation is made
A kind of artificial nest shape ground installation.Used as the basic test equipment that aircraft is developed, Flow Field in Wind Tunnel quality is to ensure test
Model obtains the core of precision data, especially in the most sensitive transonic speed fast domain of flight vehicle aerodynamic performance change, flow field
Quality is particularly important, and the slight change of flow field quality all can cause significantly change to test model aerodynamic data.For this purpose, ensureing
Transonic wind tunnel flow field quality is stable and calibration is the basic demand for safeguarding wind-tunnel, needs to carry out the stage to transonic wind tunnel flow field
Property measurement and calibrate.
In transonic wind tunnel flow field quality, space flow field symmetry is an important indicator, and Typical requirements are wind-tunnel stream
The symmetry of field is outstanding enough, and the full symmetric interference to model-test data that more levels off to is also less.However, all by wind-tunnel
Many objective condition interference, wind-tunnel space flow field is extremely difficult to full symmetric ideal standard, and solution is to spatial flow
Field symmetry is debugged and measured, and acquisition meets the flow field of GJB index.In model test, by spatial flow
Field asymmetry parameter carries out test data amendment, and acquisition approaches the model aerodynamic parameter of true value.In above procedure, to space flow field
Symmetry is measured according to test objective, can divide into comprehensive space flow field symmetry measurement and local space flow field symmetry is surveyed
Amount, wherein, the local space flow field comprising model area is the emphasis of flow field survey.
Traditionally, transonic wind tunnel space flow field symmetry is measured using stagnation pressure cross framed bent, method is to keep watch
Hole test section measured zone is divided into vertically some equidistant sections, the pressure measxurement in a section is once carried out, then to total
Pressure cross framed bent is surveyed the pressure distribution data in section and is processed, and obtains the flow field symmetry ginseng of test chamber different cross section
Numerical value.Although the method can realize test section Zone Full vertically or regional area by the change of measured zone
Space flow field symmetry is measured, and but there is also the shortcomings of measuring more, relatively costly train number, state complex, also, the method is also
Presence is unable to simulated test model under pitch orientation motion state to the deficiency of local space flow field measurement, is unfavorable for part
The analysis and process of the positive and negative dress test data difference of model.In this context, invented a kind of measurement of use cone cylinder model across
The symmetric simple and easy method in velocity of sound wind-tunnel local space flow field, the method overcomes using stagnation pressure cross framed bent measurement space flow field
Symmetric shortcoming, can realize covering the local space flow field symmetry measurement of model area along pitch orientation.
The content of the invention
In order to overcome the disadvantages mentioned above of prior art, the present invention to propose a kind of measurement transonic wind tunnel test section spatial flow
The symmetric simple and easy method in field, for carrying out the symmetry measurement of transonic wind tunnel test section local space flow field using existing method
When, it is impossible to along the problem of pitch orientation measurement, the higher, state complex of experimentation cost etc., there is provided one kind measurement transonic wind tunnel examination
Test section symmetric simple and easy method in local space flow field.The present invention can as early as possible obtain local space on the basis of accurate, reliable
Flow field symmetry result, is beneficial to impact analysis of the local space flow field symmetry to result of the test, with preferably using front
Scape.
The technical solution adopted for the present invention to solve the technical problems is：One kind measurement transonic wind tunnel test section spatial flow
The symmetric simple and easy method in field, comprises the steps：
The first step, on test section wallboard install wind-tunnel angle of attack mechanism, cone cylinder model is installed on wind-tunnel angle of attack mechanism；
Second step, space symmetr calibration of angle of attack is carried out to cone cylinder model；
3rd step, ladder manometric test is carried out under test Mach number, collection test chamber is flowing stagnation pressure P0It is right with each
Claim the pressure value P of each piezometric surface pressure tap of cone cylinder model under state of angle of attacki；
4th step, the pressure for calculating the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attack
Recovery coefficient Pi/P0With Mach number Mi；
5th step, the P for drawing the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attacki/P0
It is worth the pressure-recovery factor distribution curve with the slenderness ratio X/D change of cone cylinder, and MiIt is worth with the slenderness ratio X/D change of cone cylinder
Mach Number Distribution curve；
Under 6th step, calculating space symmetr state of angle of attack, cone cylinder model is passed judgment on the effective pressure tap of piezometric surface and is met in difference
P during anglei/P0And MiMean value [P/P0]jav[M]jav, then calculate residual quantity Δ [P/P0]avWith Δ [M]av, so as to obtain
Weigh the test section local space flow field asymmetry parameter value of cone cylinder model measurement in space symmetr angle.
Compared with prior art, the positive effect of the present invention is：The present invention is using cone cylinder model to local space flow field
It is a kind of effective ways of easy realization that symmetry is measured, and can meet the positive and negative dress test data difference investigation of model, examination
Test a section needs for local space flow field detection.The main thought of the present invention is as follows：Have that rigidity is big, pressure measurement using cone cylinder model
It is stable, the characteristics of High Mach number can be carried and test, using straight joint and adapter wind-tunnel angle of attack mechanism is installed on, carry out some groups
The ladder manometric test of the space symmetr angle of attack, by pressure measurement data analysis local space flow field symmetry.Carrying out data processing
When, the present invention under space symmetr state of angle of attack, at the pressure measurement data of cone cylinder model outside (or inner side) piezometric surface
Reason, is converted into Mach number and pressure-recovery factor, residual quantity process is carried out, will pass through the residual quantity evaluation test section local space stream
Field symmetry quality.The number of times for starting train number can be effectively reduced using the present invention, experimentation cost is reduced, is easy to test section office
Portion's space flow field symmetry is used for quickly detecting and analyzes.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is transonic wind tunnel test section local space flow field symmetry measuring method schematic diagram, wherein：1 is test section
Wallboard；2 is angle of attack mechanism；3 is straight joint；4 is adapter；5 is cone cylinder model.
Fig. 2 is the effective pressure tap of piezometric surface on the outside of cone cylinder model under space symmetry angle ± 2 ° state in embodiment 1
Pressure-recovery factor distribution curve P/P0～X/D schemes.
Fig. 3 is the effective pressure tap of piezometric surface on the outside of cone cylinder model under space symmetry angle ± 2 ° state in embodiment 1
Mach Number Distribution curve M～X/D figures.
Fig. 4 is the effective pressure tap of piezometric surface on the outside of cone cylinder model under space symmetry angle ± 4 ° state in embodiment 1
Pressure-recovery factor distribution curve P/P0～X/D schemes.
Fig. 5 is the effective pressure tap of piezometric surface on the outside of cone cylinder model under space symmetry angle ± 4 ° state in embodiment 1
Mach Number Distribution curve M～X/D figures.
Specific embodiment
As shown in figure 1, a kind of measure the symmetric simple and easy method of transonic wind tunnel test section space flow field, including following step
Suddenly：
The first step, wind-tunnel angle of attack mechanism 2 is arranged on test section wallboard 1, using straight joint 3 and adapter 4 by appearance
The cone cylinder model 5 smooth, pressure tap aeration and air-tightness are qualified is installed on wind-tunnel angle of attack mechanism 2, and pressure tap is carried out
Connection and detection, quality reaches criterion of acceptability；
The cone cylinder model is the common apparatus of high-speed wind tunnel flow field survey.
Criterion of acceptability is that the pressure tap of normal reading counts 98% counted not less than total pressure measurement, and there are no two or two
Adjacent pressure tap surveys number exception more than individual.
Second step, space symmetr calibration of angle of attack is carried out to cone cylinder model：
The angle of attack is to pass judgment on the symmetric some groups of space symmetrs angle ± α in test section local space flow field.
Calibration of angle of attack is to use the actual angle of attack of dipmeter survey cone cylinder model 5, then by the adjustment of angle of attack mechanism 2 cone
The actual angle of attack of type cylinder models is adjusted to the process being equal to space symmetr angle ± α phases.Dipmeter is also that high-speed wind tunnel is general
Angle measuring instrument.
3rd step, ladder manometric test is carried out under test Mach number, collection test chamber is flowing stagnation pressure P0It is right with each
Claim the pressure value P of each piezometric surface pressure tap of cone cylinder model under state of angle of attacki；
4th step, the pressure for calculating the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attack
Recovery coefficient Pi/P0With Mach number Mi；
In formula：MiPressure tap Mach number is referred to, i.e., according to each effective pressure tap passed judgment on piezometric surface of cone cylinder model
Pressure measurement data calculate Mach number, Pi/P0The pressure-recovery factor of each effective pressure tap is referred to, n refers to the effective pressure measurement of piezometric surface
Point sum；
Pass judgment on the outside piezometric surface that piezometric surface is the cone cylinder model under each group space symmetr state of angle of attack, or inner side pressure measurement
Face, the lower piezometric surface of concrete correspondence positive incidence state and the upper piezometric surface of negative state of angle of attack, or the upper piezometric surface of positive incidence state
With the lower piezometric surface of negative state of angle of attack.When effectively pressure tap is cone cylinder model zero degree angle of attack state, exclude by nose cone and shoulder
After the leading portion pressure tap of interference, whole pressure taps of remaining stage casing and back segment.
5th step, the P for drawing the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attacki/P0
It is worth the pressure-recovery factor distribution curve P/P with the slenderness ratio X/D change of cone cylinder0～X/D, and MiValue is with cone cylinder slenderness ratio
The Mach Number Distribution curve M～X/D of X/D changes, will pass through curve local space flow field symmetry is intuitively analyzed；
Under 6th step, calculating space symmetr state of angle of attack, cone cylinder model is passed judgment on the effective pressure tap of piezometric surface and is met in difference
P during anglei/P0And MiMean value [P/P0]jav[M]jav, then calculate residual quantity Δ [P/P0]avWith Δ [M]av, weighed
The test section local space flow field asymmetry parameter value of cone cylinder model measurement in space symmetr angle, will pass through the parameter value
Quantitative analysis space flow field symmetry quality.
Δ[P/P0]av=[P/P0]1av-[P/P0]2av (4)
Δ[M]av=[M]1av-[M]2av (5)
In the formula (2), [P/P0]javRefer to that the pressure that the effective pressure tap of piezometric surface is passed judgment under the space symmetr angle of attack is extensive
Complex coefficient mean value, j represents angle of attack different conditions, and assignment 1 represents positive incidence, and assignment 2 represents the negative angle of attack；In the formula (3),
[M]javRefer to the Mach number mean value that the effective pressure tap of piezometric surface is passed judgment under the space symmetr angle of attack, j meanings and the same formula of assignment
(2)；In the formula (4), Δ [P/P0]avUnder referring to space symmetr state of angle of attack, the pressure of the effective pressure tap of piezometric surface is passed judgment on
Recovery coefficient mean value residual quantity；In the formula (5), Δ [M]avUnder referring to space symmetr state of angle of attack, piezometric surface is passed judgment on effective
The Mach number mean value residual quantity of pressure tap.
Embodiment 1：
The present invention uses cone cylinder model, under the difference symmetry angle state of transonic wind tunnel test section local space flow field
Pressure measxurement is carried out, under each space symmetr angle state is obtained respectively, (or inner side) piezometric surface is effective on the outside of cone cylinder model
The pressure distribution data of pressure tap, draws pressure-recovery factor distribution P/P0～X/D curve maps and Mach Number Distribution M～X/D are bent
Line chart, is calculated using formula, is obtained and is weighed the symmetric parameter, Δ [P in local space flow fieldi/P0]avWith Δ [M]avData.Specifically
Realized by following data processing method.
By taking 2.4 meters of transonic wind tunnel cone cylinder model ladder manometric tests as an example, test Mach number 0.7, testing the angle of attack is
0 ° and the space symmetr angle of attack ± 2 °, ± 4 °, obtained in space symmetr angle by piezometric surface pressure measurement data on the outside of cone cylinder model
Local space flow field symmetry result.Cone cylinder model is obtained after pressure measurement data, draws pressure-recovery factor distribution P/P0～X/D
Curve and Mach Number Distribution M～X/D curves as shown in Figures 2 to 5, data processing are carried out using formula (1) to formula (5).By
Cone cylinder model pressure tap Data Processing Method has similitude under each symmetry angle state in space, is met with space symmetr
It is described in detail as a example by piezometric surface pressure tap test data on the outside of the cone cylinder model of angle ± 2 ° state.
Pressure-recovery factor P of the cone cylinder model piezometric surface pressure tap under each state of angle of attack is obtained using formula (1)i/P0
With Mach number Mi。
According to cone cylinder model pressure measurement data and the contrast of noiseless test data has been obtained under 0 ° of state of angle of attack, cone cylinder is passed judgment on
Model piezometric surface is effective pressure tap in the later pressure tap in X/D >=4.
According to obtaining data Pi/P0And MiDraw the pressure-recovery factor distribution P/P of piezometric surface on the outside of cone cylinder model0~
X/D curve maps and Mach Number Distribution M～X/D curve maps, as shown in Figures 2 and 3.
It is average the effective pressure tap of piezometric surface pressure-recovery factor at+2 ° on the outside of cone cylinder model to be calculated using formula (2)
Value [P/P0]1av, while pressure-recovery factor mean value [P/P when calculating -2 °0]2av。
The effective pressure tap of piezometric surface Mach number mean value at+2 ° on the outside of cone cylinder model is calculated using formula (3)
[M]1av, while Mach number mean value [M] when calculating -2 °2av。
Using the effective pressure tap of piezometric surface on the outside of formula (4) calculating cone cylinder model under ± 2 ° of space symmetr state of angle of attack
Average pressure recovery coefficient residual quantity Δ [P/P0]av。
Using the effective pressure tap of piezometric surface on the outside of formula (5) calculating cone cylinder model under ± 2 ° of space symmetr state of angle of attack
Average Mach number residual quantity Δ [M]av。
The result of calculation of 1 pair of local space flow field symmetry measurement of embodiment see the table below shown in 1.
The result of calculation of table 1
| α/° | Δ[P/P0]av | Δ[M]av |
| ±2° | 0.00022 | -0.00035 |
| ±4° | -0.00060 | 0.00092 |
Relative to prior art, the present invention realizes the local space flow field symmetry for covering model area along pitch orientation
Measurement, can effectively reduce the number of times for starting train number in test, reduce experimentation cost, be easy to test section local space flow field pair
Title property is used for quickly detecting and analyzes.
Claims (9)
- It is 1. a kind of to measure the symmetric simple and easy method of transonic wind tunnel test section space flow field, it is characterised in that：Including following step Suddenly：The first step, on test section wallboard install wind-tunnel angle of attack mechanism, cone cylinder model is installed on wind-tunnel angle of attack mechanism；Second step, space symmetr calibration of angle of attack is carried out to cone cylinder model；3rd step, ladder manometric test is carried out under test Mach number, collection test chamber is flowing stagnation pressure P0With each symmetrical angle of attack The pressure value P of each piezometric surface pressure tap of cone cylinder model under statei；4th step, the pressure recovery for calculating the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attack FACTOR Pi/P0With Mach number Mi；5th step, the P for drawing the effective pressure tap of cone cylinder model judge piezometric surface under each group space symmetr state of angle of attacki/P0Value with The pressure-recovery factor distribution curve of cone cylinder slenderness ratio X/D change, and MiIt is worth the Mach with the slenderness ratio X/D change of cone cylinder Number distribution curve；Under 6th step, calculating space symmetr state of angle of attack, cone cylinder model passes judgment on the effective pressure tap of piezometric surface in the different angles of attack Pi/P0And MiMean value [P/P0]jav[M]jav, then calculate residual quantity Δ [P/P0]avWith Δ [M]av, so as to be weighed The test section local space flow field asymmetry parameter value of cone cylinder model measurement in space symmetr angle.
- 2. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：The cone cylinder model is arranged on wind-tunnel angle of attack mechanism by straight joint and adapter.
- 3. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：The pressure tap aeration of the cone cylinder model and air-tightness need to meet the pressure tap counting of normal reading and be not less than The 98% of total pressure measurement points, and there is no two or more adjacent pressure taps survey number exceptions.
- 4. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：It is to the method that cone cylinder model carries out space symmetr calibration of angle of attack described in second step：Bored using dipmeter survey The actual angle of attack of type cylinder models, then cause the actual angle of attack of cone cylinder model to be equal to space symmetr angle by adjusting wind-tunnel angle of attack mechanism Degree.
- 5. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：Mach number M described in 4th stepiComputing formula it is as follows：In formula：Pi/P0The pressure-recovery factor of each effective pressure tap is referred to, n refers to the effective pressure tap sum of piezometric surface.
- 6. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：The outside pressure measurement that piezometric surface refers to the cone cylinder model under each group space symmetr state of angle of attack is passed judgment on described in 4th step Face or inner side piezometric surface.
- 7. one kind according to claim 6 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：Piezometric surface is passed judgment on described in 4th step includes the lower piezometric surface of positive incidence state and the upper piezometric surface of negative state of angle of attack, Or the upper piezometric surface and the lower piezometric surface of negative state of angle of attack of positive incidence state.
- 8. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：When effective pressure tap refers to cone cylinder model zero degree angle of attack state described in 4th step, exclusion is done by nose cone and shoulder Whole pressure taps of remaining stage casing and back segment after the leading portion pressure tap disturbed.
- 9. one kind according to claim 1 measures the symmetric simple and easy method of transonic wind tunnel test section space flow field, its It is characterised by：[the P/P0]jav、[M]javWith Δ [P/P0]av、Δ[M]avComputing formula it is as follows：Δ[P/P0]av=[P/P0]1av-[P/P0]2avΔ[M]av=[M]1av-[M]2avWherein：J represents angle of attack different conditions, and assignment 1 represents positive incidence, and assignment 2 represents the negative angle of attack.
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| CN112016164A (en) * | 2020-09-09 | 2020-12-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerospace model flight test layout, and axisymmetric nose cone region configuration and design method thereof |
| CN112556971A (en) * | 2020-12-21 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring length of interference zone of transonic wind tunnel support system |
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
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| CN112016164B (en) * | 2020-09-09 | 2022-07-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerospace model flight test layout, and axisymmetric nose cone region configuration and design method thereof |
| CN112556971A (en) * | 2020-12-21 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring length of interference zone of transonic wind tunnel support system |
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN114608792B (en) * | 2022-05-10 | 2022-07-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
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