CN110455490A - Method and device for calculating supersonic velocity and hypersonic velocity wind tunnel flow field turbulence - Google Patents
Method and device for calculating supersonic velocity and hypersonic velocity wind tunnel flow field turbulence Download PDFInfo
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Abstract
The embodiment of the invention discloses a method and a device for calculating the turbulence degree of a supersonic velocity and hypersonic velocity wind tunnel flow field, which are used for acquiring original total pressure data after a wind tunnel flow field shock wave, and decomposing the original total pressure data at each moment into wave-rear total pressure data without pulsation and actual wave-rear total pressure pulsation data; respectively calculating actual wavefront static pressure pulsation data corresponding to each actual wave-rear total pressure pulsation data according to a pressure pulsation conversion coefficient corresponding to a wind tunnel flow field obtained in advance and each actual wave-rear total pressure pulsation data at each moment; dividing each actual total pressure pulsation datum after wave generation into a plurality of data segments according to characteristic time; and calculating the average value of the wave front static pressure of the wind tunnel flow field in a preset time period according to the average value of the wave rear total pressure data without pulsation and a first preset formula, and calculating the turbulence degree corresponding to each data segment according to the average value of the wave front static pressure and each actual wave front static pressure pulsation data and a second preset formula. The invention can improve the calculation precision of the turbulence degree.
Description
Technical field
The present invention relates to Flow Field in Wind Tunnel technical field more particularly to a kind of supersonic and hypersonic Flow Field in Wind Tunnel turbulivitys
Calculation method and device.
Background technique
Wind-tunnel is the capital equipment of the expansion bottom surface simulated experiment such as aircraft, and the dummy vehicle obtained in wind-tunnel pneumatically counts
According to being foundation and the basis of Flight Vehicle Design and the following expansion flight test.Wind Tunnel Turbulence Spectral Analyzer mobility is measurement wind tunnel experiment section gas
A kind of standard of flow velocity degree degree of pulsatility.In supersonic speed or hypersonic wind tunnel, hot-wire measurement relative difficulty, and measurement result
It is the pulsation of flow, causes the assessment to turbulivity not accurate enough.In recent years, it is found in hypersonic aircraft development, according to
Carry out flight test according to ground supersonic speed/hypersonic wind tunnel experimental result, many flight tests is caused to fail.To find out its cause,
Supersonic speed/hypersonic wind tunnel flow field turbulivity usually than aircraft live flying when flight environment of vehicle in incoming flow turbulivity it is high
1-2 magnitude, causing ground wind tunnel experiment and live flying to test, there are bigger differences.Therefore, the existing wind-tunnel stream of accurate evaluation
Field turbulivity, the influence that research turbulivity generates ground experiment are paid close attention in current ultrasonic speed/hypersonic flight research
One problem.
Summary of the invention
It is an object of the invention to provide a kind of supersonic and hypersonic Flow Field in Wind Tunnel for the deficiency in traditional technology
The calculation method and device of turbulivity.
In one embodiment, the present invention provides a kind of calculating sides of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity
Method, comprising:
Obtain the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and by the original stagnation pressure number at each moment
According to being decomposed into after the wave without pulsation stagnation pressure microseismic data after stagnation pressure data and actual wave；
According to the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance and each actual wave at each moment
Stagnation pressure microseismic data afterwards calculates separately the corresponding actual wavefront static pressure microseismic data of stagnation pressure microseismic data after each actual wave；
Stagnation pressure microseismic data after each actual wave is divided into multiple data segments according to the characteristic time chosen in advance；
Flow Field in Wind Tunnel is calculated pre- according to the first preset formula according to the average value of stagnation pressure data after the wave respectively without pulsation
If the average value of corresponding wavefront static pressure in the period, and pulsed according to the average value of wavefront static pressure and each actual wavefront static pressure
Data calculate the corresponding turbulivity of each data segment according to the second preset formula.
In a specific embodiment, the characteristic time is obtained based on following steps:
The characteristic time chosen in advance is obtained based on following steps:
The wind tunnel experiment section of the physical features length and Flow Field in Wind Tunnel for the target object specified in acquisition Flow Field in Wind Tunnel
Uniform incoming flow speed；
Using the ratio of physical features length and uniform incoming flow speed as the characteristic time.
In a specific embodiment, the second preset formula are as follows:
Wherein, I indicates the corresponding turbulivity of each data segment,Indicate corresponding wavefront static pressure in preset time period
Average value；P'1Indicate actual wavefront static pressure microseismic data.
In a specific embodiment, the first preset formula are as follows:
Wherein,Indicate the average value of wavefront static pressure in preset time period；Ma1Indicate the Mach number of Flow Field in Wind Tunnel；γ table
Show specific heats of gases ratio；Indicate the average value respectively without stagnation pressure data after the wave pulsed.
In a specific embodiment, the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance is based on following
Step obtains:
According to free stream Mach number of the Flow Field in Wind Tunnel got under current working, shock wave front stagnation pressure, Flow Field in Wind Tunnel total temperature,
And default wavefront static pressure microseismic data, by the numbered analog simulation of Flow Field in Wind Tunnel obtain prediction wave after stagnation pressure microseismic data；
The ratio of stagnation pressure microseismic data after default wavefront static pressure microseismic data and prediction wave is converted as pressure fluctuation and is
Number.
In a specific embodiment, further includes:
Fourier transformation is carried out according to the corresponding time interval of each data segment and turbulivity, obtains Flow Field in Wind Tunnel pre-
If the frequency spectrum and power spectrum of turbulivity in the period.
In a specific embodiment, the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave are obtained, and
The original stagnation pressure data at each moment are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave,
Include:
Original stagnation pressure data are pre-processed to obtain without stagnation pressure data after the wave pulsed；
Stagnation pressure data obtain stagnation pressure microseismic data after actual wave after original stagnation pressure data to be subtracted to the wave for being free of pulsation.
In a specific embodiment, pretreatment include following any pretreatment: fitting of a polynomial, wavelet decomposition with
And empirical mode decomposition.
On the other hand, the embodiment of the invention also provides a kind of calculating of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity
Device, comprising:
Data acquisition process module, for obtaining the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and
The original stagnation pressure data at each moment are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave；
Pulsating quantity conversion module, for according to the corresponding pressure fluctuation conversion coefficient of Flow Field in Wind Tunnel obtained in advance and often
Stagnation pressure microseismic data after each actual wave at one moment calculates separately the corresponding practical wave of stagnation pressure microseismic data after each actual wave
Preceding static pressure microseismic data；
Segmentation module, it is multiple for stagnation pressure microseismic data after each actual wave to be divided into according to the characteristic time chosen in advance
Data segment；
Turbulivity computing module, for the average value according to stagnation pressure data after the wave respectively without pulsation according to the first default public affairs
Formula calculates the average value of Flow Field in Wind Tunnel corresponding wavefront static pressure within a preset period of time, and according to the average value of wavefront static pressure and
Each actual wavefront static pressure microseismic data calculates the corresponding turbulivity of each data segment according to the second preset formula.
On the other hand, the embodiment of the invention also provides a kind of computer equipment, including memory and processor, memories
It is stored with computer program, processor realizes the meter of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity when executing computer program
The step of calculation method.
A technical solution in above-mentioned technical proposal is had the following advantages and beneficial effects:
The calculation method and device of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity of the invention, by preset time
Original stagnation pressure data in section after shock wave carry out pretreatment and decomposite without total after stagnation pressure data after the wave pulsed and actual wave
Microseismic data is pressed, influence of the non-stationary signal to turbulivity is calculated can be eliminated.Further, each moment is obtained by conversion
The corresponding actual wavefront static pressure microseismic data of stagnation pressure microseismic data after actual wave can avoid directly measurement wind-tunnel wavefront static pressure essence
Spend the problem of low inaccuracy.Further, stagnation pressure microseismic data after the actual wave at each moment is segmented according to the characteristic time, from
And it can calculate and analyze the rule that Flow Field in Wind Tunnel turbulivity and turbulivity change over time.Various embodiments of the present invention may make
The calculated result of Flow Field in Wind Tunnel turbulivity improves computational accuracy closer to truth, while can be analysis turbulivity to wind
Hole experimental result influences to provide more detailed data support.
Detailed description of the invention
In order to illustrate more clearly of technical solution of the present invention, letter will be made to attached drawing needed in the embodiment below
It singly introduces, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as to the present invention
The restriction of protection scope.In various figures, part is similarly comprised using similar number.
Fig. 1 shows the process of the calculation method of the supersonic and hypersonic Flow Field in Wind Tunnel turbulivity of the embodiment of the present invention
Schematic diagram；
Fig. 2 shows the original stagnation pressure data and curves schematic diagrames after shock wave in the embodiment of the present invention；
Fig. 3 shows the curve synoptic diagram of stagnation pressure data after the wave without pulsation in the embodiment of the present invention；
Fig. 4 shows the curve synoptic diagram of stagnation pressure microseismic data after actual wave in the present invention；
Fig. 5 shows the structure of the computing device of the supersonic and hypersonic Flow Field in Wind Tunnel turbulivity of the embodiment of the present invention
Schematic diagram.
Specific embodiment
Below in conjunction with attached drawing in the embodiment of the present invention, technical solution in the embodiment of the present invention carries out clear, complete
Ground description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.
The component of embodiments of the present invention, which are generally described and illustrated herein in the accompanying drawings can be come with a variety of different configurations
Arrangement and design.Therefore, requirement is not intended to limit to the detailed description of the embodiment of the present invention provided in the accompanying drawings below
The scope of the present invention of protection, but it is merely representative of selected embodiment of the invention.Based on the embodiment of the present invention, this field skill
Art personnel every other embodiment obtained without making creative work belongs to the model that the present invention protects
It encloses.
Hereinafter, term " includes ", " having " and its cognate that can be used in various embodiments of the present invention are only
It is intended to mean that special characteristic, number, step, operation, the combination of element, component or aforementioned item, and is understood not to first
Exclude the combined presence or increase by one of one or more other features, number, step, operation, element, component or aforementioned item
A or more feature, number, step, operation, element, component or aforementioned item combination a possibility that.
In addition, term " first ", " second ", " third " etc. are only used for distinguishing description, it is not understood to indicate or imply
Relative importance.
Unless otherwise defined, otherwise all terms (including technical terms and scientific terms) used herein have and this
The identical meaning of the various normally understood meanings of embodiment one skilled in the art of invention.The term (such as exists
The term limited in the dictionary generally used) it is to be interpreted as that there is contain identical with situational meaning in the related technical field
Justice and Utopian meaning or meaning too formal will be interpreted as having, unless in various embodiments of the present invention
It is clearly defined.
For wind-tunnel generally with Mach number Ma classification, 1.4 < Ma < 5 are supersonic wind tunnel, and Ma >=5 are hypersonic wind tunnel.It passes
In system technology, in the measurement of supersonic speed and hypersonic wind tunnel flow field turbulivity, through measuring wind-tunnel frequently with pressure fluctuation
Turbulivity, Flow Field in Wind Tunnel turbulivity be measure one of Flow Field in Wind Tunnel quality and the important parameter of Wind Tunnel Data reliability.
In the method for pressure measurement data assessment Flow Field in Wind Tunnel turbulivity, in addition to using in more accurate method measurement Flow Field in Wind Tunnel
Pressure fluctuation is outer (such as using sensitivity with high, the faster sensor of frequency response), how based on original pressure data calculating wind-tunnel
Turbulivity is also an important link.In traditional technology, turbulivity is calculated based on following formula:
Here I is Flow Field in Wind Tunnel turbulent flow, p02It is that (i.e. sensor measurement obtains stagnation pressure after the shock wave at a certain moment in certain time
The pressure data arrived), p0′2It is the pulsating quantity of stagnation pressure after shock wave,It is the average value of stagnation pressure after shock wave in this time.But
This calculation method can only for stable pressure signal (i.e. during wind tunnel operation flow field pressure, do not considering to pulse
In the case where be basically unchanged).However most of wind-tunnel practical operation situations are fluid field pressures it is possible that changing up and down,
As pressure is gradually increasing or is gradually reduced or the cyclically-varying of rise and fall.Assuming that fluid field pressure is during wind tunnel operation
Uniformly increase, even if fluid field pressure does not occur pulsatile change (thinking that turbulivity is zero), but by above-mentioned formula still can based on
The turbulivity for obtaining non-zero is calculated as a result, this is not inconsistent with truth.
It on the other hand, is at present that the signal that will entirely measure calculates to the calculating of turbulivity, what is obtained is entirely to survey
Average turbulivity during amount, the parameter can be used as the standard of Flow Field in Wind Tunnel quality estimating, but using the data as foundation
When analyzing influence of the turbulivity to wind tunnel experimental results, there is no the frequency domains for considering turbulivity and time domain specification can produce to experiment
What raw influence, such analysis result there is a problem.It may cause the different wind tunnel experiments with identical turbulence value,
Measurement obtains result, and there are difference.Although having there is research to consider the frequency characteristic in Wind Tunnel Turbulence Spectral Analyzer mobility power spectrum,
But removing frequency domain characteristic influences outer, shadow of the Flow Field in Wind Tunnel turbulivity time domain specification (turbulivity changes over time) to experimental result
Sound is also very important.Even if the frequency domain characteristic of turbulivity is consistent, the difference that the real-time turbulivity of wind-tunnel changes over time is also resulted in
The difference of experimental result.
Referring to Fig. 1 to Fig. 4, abscissa X indicates the sequence number of sampled data points in Fig. 2-Fig. 4, indicates which hits
According to ordinate kPa indicates pressure.In one embodiment, the present invention provides a kind of supersonic and hypersonic Flow Field in Wind Tunnel
The calculation method of turbulivity, comprising:
Step S110: obtaining the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and by each moment
Original stagnation pressure data are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave.
It is the curve synoptic diagram of the original stagnation pressure data after the shock wave got within a preset period of time such as Fig. 2, each
Sampled data points indicate an original stagnation pressure data.In order to which the non-stationary for eliminating fluid field pressure signal in Flow Field in Wind Tunnel as far as possible is special
Property, therefore, the original stagnation pressure data after the shock wave at each moment are pre-processed, are decomposed into stagnation pressure number after the wave without pulsation
According to stagnation pressure microseismic data after actual wave.It is decomposited at any time as Fig. 3 is shown from the original stagnation pressure data after the shock wave of Fig. 2
Between change without stagnation pressure data after pulsating wave, each sampled data points indicate one without stagnation pressure data after pulsating wave.Such as Fig. 4
It shows from stagnation pressure microseismic data, each sampled data after the actual wave that the original stagnation pressure data after the shock wave of Fig. 2 decomposite
Point indicates stagnation pressure microseismic data after an actual wave.
The embodiment of the present invention can eliminate in the original stagnation pressure data after shock wave that there are non-stationary variations to calculating turbulivity
Influence, help to optimize the calculating and precision to turbulivity.
In a specific embodiment, the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave are obtained, and
The original stagnation pressure data at each moment are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave,
Include:
Step S2: original stagnation pressure data are pre-processed to obtain without stagnation pressure data after the wave pulsed.
In a specific embodiment, pretreatment include following any pretreatment: fitting of a polynomial, wavelet decomposition with
And empirical mode decomposition.
For example, the original stagnation pressure data after shock wave are carried out fitting of a polynomial, using the data in matched curve as being free of
Stagnation pressure data (such as the fitting of 5 rank multinomials, fitting of 7 rank multinomials etc.) after the wave of pulsation；Or to the original stagnation pressure number after shock wave
It is the high-frequency signal of low frequency signal and different layers by signal decomposition, low frequency signal is as without pulsation according to wavelet decomposition is carried out
Stagnation pressure data after wave；Or rule of thumb mode decomposition carries out adaptive-filtering by the original stagnation pressure data after shock wave, by what is obtained
Data are as stagnation pressure data after the wave without pulsation.
Wherein, the mode of fitting of a polynomial is relatively suitble to the original stagnation pressure after the shock wave for being gradually increasing or being gradually reduced
Data are handled, and wavelet decomposition and empirical mode decomposition are relatively suitble to the original stagnation pressure data after periodically variable shock wave
It is handled.
Step S4: original stagnation pressure data are subtracted to stagnation pressure after obtaining actual wave without stagnation pressure data after the wave pulsed and are pulsed
Data.
The embodiment of the present invention can in several ways the original stagnation pressure data after the shock wave to different variation tendencies carry out it is pre-
Processing, helps to improve the precision of data processing.
Step S120: each according to the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance and each moment
Stagnation pressure microseismic data after actual wave calculates separately the corresponding actual wavefront static pressure pulsation of stagnation pressure microseismic data after each actual wave
Data.
Wherein, Flow Field in Wind Tunnel corresponding pressure fluctuation conversion coefficient under each operating condition, indicates stagnation pressure microseismic data after wave
With the proportionate relationship between wavefront static pressure microseismic data.The acoustic perturbation with the angle of attack is passed through in the numerical simulation about flow field
In the analysis of shock wave process, the ratio after actual wavefront static pressure microseismic data and actual wave between stagnation pressure microseismic data is provided
Relational expression, it is as follows, the corresponding actual wavefront static pressure of stagnation pressure microseismic data after each actual wave can be obtained based on following relationship
Microseismic data:
Wherein, P '1Indicate actual wavefront static pressure microseismic data, P '2Indicate stagnation pressure microseismic data after actual wave,
It is a certain in Flow Field in Wind Tunnel for the coefficient obtained by the transmission function of pressure fluctuation after shock wave front, i.e. pressure fluctuation conversion coefficient
Determine under operating condition that it is the numerical value determined, to convert the corresponding actual wavefront static pressure arteries and veins of stagnation pressure microseismic data after actual wave
Dynamic data.
Step S130: stagnation pressure microseismic data after each actual wave is divided into multiple data according to the characteristic time chosen in advance
Section.
Characteristic time is a time span, and the selection of characteristic time is related with wind tunnel experiment model, Field Characteristics, after segmentation
Each data segment includes the data in one or more characteristic times.By stagnation pressure microseismic data after each actual wave according to preparatory choosing
The characteristic time taken is divided into multiple data segments, can be segmented in the following manner: by each reality such as unit of this feature time
Wave after stagnation pressure microseismic data be divided into multiple data segments；Or the corresponding time span of every segment data can be times of characteristic time
Number, thus by each data correspondence be divided into multistage, if the characteristic time is expressed as 1T, then every segment data corresponding time be 1T, 5T,
10T, 0.1T, 0.5T etc..The embodiment of the present invention facilitates influence of the analysis time variation to turbulivity as a result, improves analysis essence
Degree.
Stagnation pressure microseismic data after each actual wave is segmented by the embodiment of the present invention according to the characteristic time of selection, is facilitated
To the changing rule of the turbulivity changed over time and the turbulivity, to improve based on turbulivity to wind tunnel experimental results
Analysis precision.
Certain specific frequencies have a very big impact Flow Field in Wind Tunnel, such as boundary layer transition, and certain specific frequencies go out
The existing time is different, and the effect generated is also different.For example first there is certain specific frequency, Flow Field in Wind Tunnel is affected, and causes
Experimental result changes, even if the specific frequency disappears below, the influence of Flow Field in Wind Tunnel will not disappear immediately, or even under holding
It goes.Therefore, the time order and function which occurs causes flow field change less identical, and the influence to experimental result is not yet
Equally.Only one most of time averaging turbulivity result of analysis method in traditional technology and in the entire data segment time
Turbulivity corresponding spectrum distribution situation, and the influence for changing over time characteristic is ignored, it is unfavorable for tying experiment based on turbulivity
The analysis of fruit.
In a specific embodiment, the characteristic time chosen in advance is obtained based on following steps:
Step S6: the physical features length for the target object specified in Flow Field in Wind Tunnel and the wind-tunnel of Flow Field in Wind Tunnel are obtained
The uniform incoming flow speed of experimental section.
Wind tunnel experiment section is the region tested for placing model.The selection of characteristic time and wind tunnel experiment model,
Field Characteristics are related.For example, the speed U characterized by the uniform incoming flow speed of wind tunnel experiment sectionfIt indicates, with a certain physical size
As characteristic length LfIt indicates.Physical features length can select according to actual needs, and to Mr. Yu's aircraft shape, it may be selected
Length or width are as characteristic length, if paying close attention to certain fluidal texture, using certain physics length dimension of the structure as object
Characteristic length is managed, for example hypersonic aircraft compares the boundary layer flow of concern, can choose boundary layer thickness as physics
Characteristic length.
Step S8: using the ratio of physical features length and uniform incoming flow speed as the characteristic time.
The embodiment of the present invention passes through the physical features length of specified target object and the uniform incoming flow speed of wind tunnel experiment section
It spends and determines the characteristic time, help to improve the precision for calculating turbulivity, while can be analysis turbulivity to wind tunnel experimental results shadow
It rings and more detailed data support is provided.Further, with same experiments (i.e. as target object identical experiment) Comparative result
In, for the rule convenient for extracting experimental result, identical physical parameter can be chosen with the same experiments, such as the feature of target object
The uniform incoming flow speed of length and wind tunnel experiment section facilitates the analysis and and same experiments to experimental result as characteristic parameter
Result compare.
Step S140: wind-tunnel is calculated according to the first preset formula according to the average value of stagnation pressure data after the wave respectively without pulsation
The average value of flow field wavefront static pressure within a preset period of time, and according to the average value of wavefront static pressure and each actual wavefront static pressure arteries and veins
Dynamic data calculate the corresponding turbulivity of each data segment according to the second preset formula.
In a specific embodiment, the first preset formula are as follows:
Wherein,Indicate the average value of corresponding wavefront static pressure in preset time period；Ma1Indicate the Mach of Flow Field in Wind Tunnel
Number；γ indicates specific heats of gases ratio；Indicate the average value respectively without stagnation pressure data after the wave pulsed.
The present invention implements to obtain Flow Field in Wind Tunnel based on first preset formula that wavefront static pressure is averaged within a preset period of time
Value, calculating process is simple, can reduce the redundancy of program.
In a specific embodiment, the second preset formula are as follows:
Wherein, I indicates the corresponding turbulivity of each data segment,Indicate corresponding wavefront static pressure in preset time period
Average value；P'1Indicate actual wavefront static pressure microseismic data.Further, ∑ (P '1) it 2 is corresponding each reality in each data segment
Wavefront static pressure microseismic data square sum.
The embodiment of the present invention is based on corresponding each actual wavefront static pressure microseismic data in the second preset formula, each data segment
Square sum and Flow Field in Wind Tunnel corresponding wavefront static pressure within a preset period of time average value, different periods can be obtained
Turbulivity, calculate simple, the computational accuracy of turbulivity can be improved.Meanwhile facilitating turbulivity result according to each segment data
It obtains turbulivity and changes over time rule, provide more detailed data to wind tunnel experimental results influence for analysis turbulivity.
The supersonic speed of the embodiment of the present invention and the calculation method of hypersonic wind tunnel flow field turbulivity, by preset time
Original stagnation pressure data in section after shock wave carry out pretreatment and decomposite without total after stagnation pressure data after the wave pulsed and actual wave
Microseismic data is pressed, influence of the non-stationary signal to turbulivity is calculated can be eliminated.Further, each moment is obtained by conversion
It is quiet to can avoid directly measurement wind-tunnel wavefront flow field for the corresponding actual wavefront static pressure microseismic data of stagnation pressure microseismic data after actual wave
Press the problem of the low inaccuracy of precision.Further, according to the characteristic time to stagnation pressure microseismic data after the actual wave at each moment point
Section, so as to calculate and analyze the rule that Flow Field in Wind Tunnel turbulivity and turbulivity change over time.The embodiment of the present invention can make
The calculated result for obtaining Flow Field in Wind Tunnel turbulivity improves computational accuracy closer to truth, while can be analysis turbulivity pair
Wind tunnel experimental results influence to provide more detailed data support.
In a specific embodiment, further includes:
Fourier transformation is carried out according to the corresponding time interval of each data segment and turbulivity, obtains Flow Field in Wind Tunnel pre-
If the frequency spectrum and power spectrum of turbulivity in the period.
Each data segment is segmented according to the characteristic time chosen in advance, therefore, the corresponding time interval of each data segment
I.e. time span can be a characteristic time, be also possible to the multiple of characteristic time.Specifically, corresponding with each data segment
Turbulivity is sample parameter, is the sampling interval according to the corresponding time interval of each data segment and is scaled using frequency, passes through
Common function such as fourier function carries out Fourier transformation in Matlab, to calculate Flow Field in Wind Tunnel within a preset period of time
The frequency spectrum and power spectrum of turbulivity.
The supersonic speed of the embodiment of the present invention and the calculation method of hypersonic wind tunnel flow field turbulivity, based on changing over time
Turbulivity to change to obtain frequency spectrum and power spectrum by Fourier, to further obtain the rule that turbulivity changes over time
Rule, i.e. spectrum distribution and Power Spectrum Distribution, for analyze influence of the turbulivity of Flow Field in Wind Tunnel to experimental result provide it is more quasi-
True foundation.
In a specific embodiment, the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance is based on following
Step obtains:
Step S10: according to free stream Mach number, shock wave front stagnation pressure, wind-tunnel of the Flow Field in Wind Tunnel got under current working
Flow field total temperature and default wavefront static pressure microseismic data, by the numbered analog simulation of Flow Field in Wind Tunnel obtain prediction wave after stagnation pressure
Microseismic data.
According to the operating condition for the Flow Field in Wind Tunnel for carrying out wind tunnel experiment and determination, in order to obtain Flow Field in Wind Tunnel under current working more
Add accurate pressure fluctuation conversion coefficient, the numbered analog simulation experiment that can carry out Flow Field in Wind Tunnel in advance is calculated.In advance
If wavefront static pressure microseismic data can set for people, the wavefront static pressure for simulating Flow Field in Wind Tunnel is pulsed.Specifically, in numerical simulation
Parameter of the entrance boundary input Flow Field in Wind Tunnel of simulation under current working, free stream Mach number, shock wave front including Flow Field in Wind Tunnel
Stagnation pressure, Flow Field in Wind Tunnel total temperature and default wavefront static pressure microseismic data, to simulate stagnation pressure microseismic data after prediction wave.
Step S12: using the ratio of stagnation pressure microseismic data after default wavefront static pressure microseismic data and prediction wave as pressure arteries and veins
Dynamic conversion coefficient.
According to the pulsation of wavefront static pressure, the proportionate relationship after wave after stagnation pressure pulsation and shock wave front between transmission function, i.e., on
State the relational expression of embodiment:Default wavefront static pressure microseismic data is replaced by P '1, by numerical simulation mould
Stagnation pressure microseismic data substitutes P ' after the prediction wave drawn up2, as a result, by stagnation pressure arteries and veins after default wavefront static pressure microseismic data and prediction wave
The ratio of dynamic data has determined corresponding pressure fluctuation conversion under Flow Field in Wind Tunnel current working as pressure fluctuation conversion coefficient
Coefficient
The supersonic speed of the embodiment of the present invention and the calculation method of hypersonic wind tunnel flow field turbulivity, can be according to specific
Proportionate relationship after the current working and static pressure microseismic data and wave of Flow Field in Wind Tunnel between stagnation pressure microseismic data, obtains precision
Higher pressure fluctuation conversion coefficient.It can be according to stagnation pressure pulse number after actual wave to be based on the pressure fluctuation conversion coefficient
According to actual wavefront static pressure microseismic data is converted to, to utilize the average value of actual wavefront static pressure microseismic data and wavefront static pressure
Turbulivity is calculated, so that the calculated result of Flow Field in Wind Tunnel turbulivity is closer to truth.
According to the definition of turbulivity, turbulivity is calculated with pressure data, pressure data here refers to Flow Field in Wind Tunnel
Static pressure data, but supersonic speed and hypersonic wind tunnel generally use be Pitot tube measurement shock wave after stagnation pressure data.Cause
This, the turbulivity being calculated with the stagnation pressure data after shock wave is different with the turbulivity being calculated with static pressure, and is used
Static pressure and static pressure microseismic data calculate the definition for more meeting turbulivity.
Referring to Fig. 5, in one embodiment, the present invention also provides a kind of supersonic and hypersonic Flow Field in Wind Tunnel turbulent flows
The computing device of degree, comprising:
Data acquisition process module 510, for obtaining the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave,
And the original stagnation pressure data at each moment are decomposed into without stagnation pressure pulse number after stagnation pressure data after the wave pulsed and actual wave
According to.
Pulsating quantity converts module 520, for according to the corresponding pressure fluctuation conversion coefficient of Flow Field in Wind Tunnel that obtains in advance with
And stagnation pressure microseismic data after each actual wave at each moment, calculate separately the corresponding reality of stagnation pressure microseismic data after each actual wave
Border wavefront static pressure microseismic data.
Segmentation module 530, for stagnation pressure microseismic data after each actual wave to be divided into according to the characteristic time chosen in advance
Multiple data segments.
Turbulivity computing module 540, it is pre- according to first for the average value according to stagnation pressure data after the wave respectively without pulsation
If formula calculates the average value of Flow Field in Wind Tunnel wavefront static pressure within a preset period of time, and according to the average value of wavefront static pressure and each
Actual wavefront static pressure microseismic data calculates the corresponding turbulivity of each data segment according to the second preset formula.
The supersonic speed of the embodiment of the present invention and the computing device of hypersonic wind tunnel flow field turbulivity, by preset time
Original stagnation pressure data in section after shock wave carry out pretreatment and decomposite without total after stagnation pressure data after the wave pulsed and actual wave
Microseismic data is pressed, influence of the non-stationary signal to turbulivity is calculated can be eliminated.Further, each moment is obtained by conversion
The corresponding actual wavefront static pressure microseismic data of stagnation pressure microseismic data after actual wave can avoid directly measurement wind-tunnel wavefront static pressure essence
Spend the problem of low inaccuracy.Further, stagnation pressure microseismic data after the actual wave at each moment is segmented according to the characteristic time, from
And it can calculate and analyze the rule that Flow Field in Wind Tunnel turbulivity and turbulivity change over time.The embodiment of the present invention may make wind
The calculated result of hole flow field turbulivity improves computational accuracy closer to truth, while can be analysis turbulivity to wind-tunnel
Experimental result influences to provide more detailed data support.
In a specific embodiment, further includes:
Feature obtains module, for obtaining the physical features length and wind-tunnel of the target object specified in Flow Field in Wind Tunnel
The uniform incoming flow speed of the wind tunnel experiment section in flow field.
Characteristic time computing module, for using the ratio of physical features length and uniform incoming flow speed as the characteristic time.
In a specific embodiment, further includes:
Numerical Simulation module, for according to free stream Mach number under current working of the Flow Field in Wind Tunnel that gets, swash
Wavefront stagnation pressure, Flow Field in Wind Tunnel total temperature and default wavefront static pressure microseismic data, are obtained by the numbered analog simulation of Flow Field in Wind Tunnel
Stagnation pressure microseismic data after prediction wave.
Conversion coefficient computing module, for by default wavefront static pressure microseismic data and prediction wave after stagnation pressure microseismic data ratio
Value is used as pressure fluctuation conversion coefficient.
In a specific embodiment, further includes:
Conversion module is obtained for carrying out Fourier transformation according to the corresponding time interval of each data segment and turbulivity
To the frequency spectrum and power spectrum of Flow Field in Wind Tunnel turbulivity within a preset period of time.
In a specific embodiment, data acquisition process module includes:
First pretreatment unit, for being pre-processed to obtain without stagnation pressure number after the wave pulsed by original stagnation pressure data
According to.
Second pretreatment unit, for by original stagnation pressure data subtract without pulsation wave after stagnation pressure data obtain it is actual
Stagnation pressure microseismic data after wave.
The specific restriction of computing device about supersonic and hypersonic Flow Field in Wind Tunnel turbulivity may refer to above
Restriction for the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity, details are not described herein.Above-mentioned supersonic speed and
Modules in the computing device of hypersonic wind tunnel flow field turbulivity can be fully or partially through software, hardware and combinations thereof
To realize.Above-mentioned each module can be embedded in the form of hardware or independently of in the processor in computer equipment, can also be with soft
Part form is stored in the memory in computer equipment, executes the corresponding behaviour of the above modules in order to which processor calls
Make.
In one embodiment, the present invention also provides a kind of computer equipment, including memory and processor, memories
It is stored with computer program, processor realizes the meter of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity when executing computer program
The step of calculation method.
The computer equipment can be terminal, which includes the processor connected by system bus, storage
Device, network interface, display screen and input unit.Wherein, the processor of the computer equipment is for providing calculating and control ability.
The memory of the computer equipment includes non-volatile memory medium, built-in storage.The non-volatile memory medium is stored with behaviour
Make system and computer program.The built-in storage is the operation of the operating system and computer program in non-volatile memory medium
Environment is provided.The network interface of the computer equipment is used to communicate with external terminal by network connection.The computer program
A kind of calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity is realized when being executed by processor.The computer equipment
Display screen can be liquid crystal display or electric ink display screen, the input unit of the computer equipment can be display screen
The touch layer of upper covering is also possible to the key being arranged on computer equipment shell, trace ball or Trackpad, can also be external
Keyboard, Trackpad or mouse etc..
In one embodiment, a kind of computer equipment, including memory and processor are provided, is stored with meter in memory
Calculation machine program, the processor realize the side of the calculating of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity when executing computer program
Method.
In several embodiments provided herein, it should be understood that disclosed device and method can also pass through
Other modes are realized.The apparatus embodiments described above are merely exemplary, for example, flow chart and structure in attached drawing
Figure shows the system frame in the cards of the device of multiple embodiments according to the present invention, method and computer program product
Structure, function and operation.In this regard, each box in flowchart or block diagram can represent a module, section or code
A part, a part of the module, section or code includes one or more for implementing the specified logical function
Executable instruction.It should also be noted that function marked in the box can also be to be different from the implementation as replacement
The sequence marked in attached drawing occurs.For example, two continuous boxes can actually be basically executed in parallel, they are sometimes
It can execute in the opposite order, this depends on the function involved.It is also noted that in structure chart and/or flow chart
The combination of each box and the box in structure chart and/or flow chart, can function or movement as defined in executing it is dedicated
Hardware based system realize, or can realize using a combination of dedicated hardware and computer instructions.
In addition, each functional module or unit in each embodiment of the present invention can integrate one independence of formation together
Part, be also possible to modules individualism, an independent part can also be integrated to form with two or more modules.
It, can be with if the function is realized and when sold or used as an independent product in the form of software function module
It is stored in a computer readable storage medium.Based on this understanding, technical solution of the present invention is substantially in other words
The part of the part that contributes to existing technology or the technical solution can be embodied in the form of software products, the meter
Calculation machine software product is stored in a storage medium, including some instructions are used so that a computer equipment (can be intelligence
Can mobile phone, personal computer, server or network equipment etc.) execute each embodiment the method for the present invention whole or
Part steps.And storage medium above-mentioned include: USB flash disk, mobile hard disk, read-only memory (ROM, Read-Only Memory),
Random access memory (RAM, Random Access Memory), magnetic or disk etc. be various to can store program code
Medium.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, can easily think of the change or the replacement, and should all contain
Lid is within protection scope of the present invention.
Claims (10)
1. a kind of calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity characterized by comprising
Obtain the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and by the original stagnation pressure number at each moment
According to being decomposed into after the wave without pulsation stagnation pressure microseismic data after stagnation pressure data and actual wave；
According to the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance and each actual wave at each moment
Stagnation pressure microseismic data afterwards calculates separately the corresponding actual wavefront static pressure microseismic data of stagnation pressure microseismic data after each actual wave；
Stagnation pressure microseismic data after each actual wave is divided into multiple data segments according to the characteristic time chosen in advance；
The Flow Field in Wind Tunnel is calculated in institute according to the first preset formula according to the average value of stagnation pressure data after the wave respectively without pulsation
The average value of corresponding wavefront static pressure in preset time period is stated, and according to the average value of the wavefront static pressure and each reality
Wavefront static pressure microseismic data calculates the corresponding turbulivity of each data segment according to the second preset formula.
2. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 1, chooses in advance
The characteristic time is obtained based on following steps:
Obtain the physical features length for the target object specified in the Flow Field in Wind Tunnel and the wind tunnel experiment of the Flow Field in Wind Tunnel
The uniform incoming flow speed of section；
Using the ratio of the physical features length and the uniform incoming flow speed as the characteristic time.
3. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 1, which is characterized in that
Second preset formula are as follows:
Wherein, I indicates the corresponding turbulivity of each data segment,Indicate corresponding wavefront static pressure in the preset time period
Average value；P'1Indicate the actual wavefront static pressure microseismic data.
4. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 1, which is characterized in that
First preset formula are as follows:
Wherein,Indicate the average value of corresponding wavefront static pressure in the preset time period；Ma1Indicate the Mach of Flow Field in Wind Tunnel
Number；γ indicates specific heats of gases ratio；Indicate the average value respectively without stagnation pressure data after the wave pulsed.
5. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 1, which is characterized in that
The corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance is obtained based on following steps:
According to free stream Mach number of the Flow Field in Wind Tunnel got under current working, shock wave front stagnation pressure, Flow Field in Wind Tunnel total temperature,
And default wavefront static pressure microseismic data, by the numbered analog simulation of Flow Field in Wind Tunnel obtain prediction wave after stagnation pressure microseismic data；
Using the ratio of stagnation pressure microseismic data after the default wavefront static pressure microseismic data and the prediction wave as the pressure arteries and veins
Dynamic conversion coefficient.
6. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 1, which is characterized in that
Further include:
Fourier transformation is carried out according to each corresponding time interval of data segment and the turbulivity, obtains the wind-tunnel
The frequency spectrum and power spectrum of flow field turbulivity in the preset time period.
7. according to claim 1 to the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity described in 6 any one,
It is characterized in that, obtain the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and by the original at each moment
Beginning stagnation pressure data are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave, comprising:
The original stagnation pressure data are pre-processed to obtain described without stagnation pressure data after the wave pulsed；
The original stagnation pressure data are subtracted into stagnation pressure data after the wave without pulsation and obtain stagnation pressure arteries and veins after the actual wave
Dynamic data.
8. the calculation method of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity according to claim 7, which is characterized in that
The pretreatment includes following any pretreatment: fitting of a polynomial, wavelet decomposition and empirical mode decomposition.
9. a kind of computing device of supersonic and hypersonic Flow Field in Wind Tunnel turbulivity characterized by comprising
Data acquisition process module, for obtaining the original stagnation pressure data in Flow Field in Wind Tunnel preset time period after shock wave, and will be every
The original stagnation pressure data at one moment are decomposed into without stagnation pressure microseismic data after stagnation pressure data after the wave pulsed and actual wave；
Pulsating quantity conversion module, for according to the corresponding pressure fluctuation conversion coefficient of the Flow Field in Wind Tunnel obtained in advance and often
Stagnation pressure microseismic data after each actual wave at one moment calculates separately the corresponding practical wave of stagnation pressure microseismic data after each actual wave
Preceding static pressure microseismic data；
Segmentation module, it is multiple for stagnation pressure microseismic data after each actual wave to be divided into according to the characteristic time chosen in advance
Data segment；
Turbulivity computing module, by according to respectively without pulsation wave after stagnation pressure data average value according to the first preset formula based on
Calculate the average value of Flow Field in Wind Tunnel wavefront static pressure in the preset time period, and according to the average value of the wavefront static pressure with
And each actual wavefront static pressure microseismic data calculates the corresponding turbulivity of each data segment according to the second preset formula.
10. a kind of computer equipment, which is characterized in that including memory and processor, the memory is stored with computer journey
Sequence, which is characterized in that super described in any one of perform claim requirement 1 to 8 when the processor executes the computer program
The calculation method of the velocity of sound and hypersonic wind tunnel flow field turbulivity.
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