CN110686858B - Sound explosion measurement wind tunnel test data processing method - Google Patents

Sound explosion measurement wind tunnel test data processing method Download PDF

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CN110686858B
CN110686858B CN201911081250.1A CN201911081250A CN110686858B CN 110686858 B CN110686858 B CN 110686858B CN 201911081250 A CN201911081250 A CN 201911081250A CN 110686858 B CN110686858 B CN 110686858B
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杨洋
钱丰学
林学东
毛代勇
魏志
尹刚
陈学孔
王瑞波
贾智亮
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China Aerodynamics Research And Development Center
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Abstract

The invention discloses a method for processing test data of a sonic boom measurement wind tunnel, belongs to the field of aerospace wind tunnel tests, and aims to solve the problem that the conventional method for processing the test data of the sonic boom measurement wind tunnel is incomplete in the aspect of eliminating background pressure interference. The processing method comprises the following steps: A. obtaining the pressure recovery coefficient of the probe through theoretical calculation or numerical simulation according to the configuration and the opening position of the probe; B. moving the measuring probe along the axial direction of the wind tunnel, carrying out flow field calibration and obtaining a pressure value of the measuring probe along the way; C. and carrying out a model sonic boom measurement wind tunnel test to obtain the pressure measurement value of the measurement probe at each point along the way and the like. According to the method, pressure recovery coefficients and background pressure calibration data under the same wind tunnel body condition are introduced to participate in processing of sound explosion measurement wind tunnel test data, on one hand, reference pressure of overpressure value calculation can be normalized into wind tunnel incoming flow static pressure, and on the other hand, background pressure fluctuation in the sound explosion measurement wind tunnel test data can be accurately eliminated point to point.

Description

Sound explosion measurement wind tunnel test data processing method
Technical Field
The invention relates to the field of aerospace wind tunnel tests, in particular to a method for processing test data of a sonic boom measurement wind tunnel.
Background
When the running speed of the aircraft reaches supersonic speed, a series of waves generated by the appearance of the aircraft interfere with each other and influence each other in the process of spreading to a distance, and finally the front shock wave wrapping the head of the aircraft and the rear shock wave trailing the tail of the aircraft are converged into a whole. When this wave system propagates to the ground, it is perceived as two thunder-like loud sounds called a sonic boom.
As an independent test technology, the sonic boom measurement test is to acquire sonic boom characteristics generated by an aircraft in a test mode. A typical sound blast measurement wind tunnel test basic idea is as follows: keeping the attitude of the aircraft model and the vertical distance between the centroid of the aircraft model and the axis of the measuring probe unchanged, and controlling the measuring probe to penetrate through the model influence area from the position far away from the model sonic boom influence area at the upstream to the position far away from the model sonic boom influence area at the downstream along the wind tunnel incoming flow direction in the test process, thereby obtaining the change characteristic of the pressure generated when the pressure is subjected to wave system interference generated by the model under the flight path line compared with non-interference data. In the period, a reference probe is arranged at a certain fixed position with good uniformity of the wind tunnel flow field and not in the model sonic boom influence area, and the static pressure at the position is measured and used as the reference static pressure.
The sonic boom signature is generally characterized by an "overpressure value" parameter Δ P/P, which is defined as follows:
ΔP/P＝(Pp-Ps)/Ps；
wherein Pp refers to the static pressure value when a certain measuring position x is influenced by sonic boom;
ps refers to the static pressure value when a certain measurement position x is not affected by a sonic boom, i.e. the reference static pressure.
It should be noted that the above is given by a theoretical calculation formula, and in the experiment, the static pressure value when a certain measurement position x is affected by the sonic boom and not affected by the sonic boom cannot be obtained at the same time. Therefore, during a wind tunnel test, a certain position which is good in uniformity of a wind tunnel flow field and is not in a model sonic boom influence area is often selected, the static pressure Pw of the position is measured through a device, and a static pressure value when the certain measurement position x is not influenced by sonic boom is indirectly obtained through certain data processing.
Fig. 1 shows a schematic view of the measurement positions of the model, the measurement probe and the reference probe at a certain measurement position x. Pw is defined as the reference probe pressure measurement, Pp is defined as the pressure measurement when the measurement probe is within the model sonic boom influence region, and Ps is defined as the pressure measurement when the measurement probe is outside the model sonic boom influence region.
Currently, the conventional data processing method is as follows.
Under ideal conditions and under the conditions of fixed Mach number and incoming flow static pressure, the overpressure value of a certain measurement position x in the model sonic boom influence area is obtained through a formula (1):
Figure BDA0002264032830000011
wherein, (DeltaP/P)TRUEThe overpressure value of a certain measurement position x in a model sonic boom influence area is shown;
pp is the static pressure value when a certain measuring position x is influenced by sonic boom;
ps refers to the static pressure value when the same measurement location x is not affected by a sonic boom, i.e. the reference static pressure.
Since the static pressure at a certain measurement position under and without the influence of the model sonic boom cannot be measured at the same time, the actually obtained overpressure value at a certain measurement position x is obtained by the formula (2):
Figure BDA0002264032830000021
wherein, (DeltaP/P)MEASUREDThe measured overvoltage value is an actually measured overvoltage value of a certain measuring position x in a model sonic boom influence area;
pp is the static pressure value when a certain measuring position x is influenced by sonic boom;
pw is a static pressure value which has good uniformity in a wind tunnel flow field and is not at a certain fixed position in a model sonic boom influence area.
Combining the formulas (1) and (2), the actual overpressure value of a certain measurement position x in the model sonic boom influence area is obtained through the formula (3):
Figure BDA0002264032830000022
wherein, (DeltaP/P)MEASURED,0The measured overpressure value is measured when the measuring probe is positioned outside the model sonic boom influence area. Because the installation positions of the measuring probe and the reference probe are different, and the inflow static pressure distribution of the whole test section has axial gradient, therefore, (delta P/P)MEASURED,0≠0。
Ps is obtained by the formula (4):
Figure BDA0002264032830000023
through the formulas (3) and (4), the overpressure value of a certain measuring position x in the model sonic boom influence area can be obtained.
Fig. 2 shows a schematic diagram of an unmodified typical sonic boom signature. When the measuring position is in the interval 1, the measuring probe is outside the model sonic boom influence area, but the difference of the incoming static pressure of different installation positions of the measuring probe and the reference probe causes (delta P/P)MEASURED,0Not equal to 0. The interval 2 corresponds to the measurement probe being in the model sonic boom influence region.
Compared with the overpressure value obtained by directly calculating the measured value of the reference probe, the overpressure value obtained by the data processing method corrects errors caused by uneven static pressure distribution of the test section and different installation positions of the reference probe and the measurement probe, and improves the accuracy of the test data of the sonic boom measurement wind tunnel to a certain extent.
Disclosure of Invention
However, the above data processing method has two problems as follows:
1) according to the basic principle of aerodynamics, supersonic incoming flow generates compression waves when passing through the head of a probe, and then the pressure is gradually restored to the static pressure of the incoming flow when being transmitted downstream along the surface direction of the probe; however, for different probe configurations and opening positions, the pressure recovery conditions at the pressure measuring holes of the probes are different, and the pressure measuring value of the probe with a certain configuration at the position of the pressure measuring hole is not the inflow static pressure, so that the calculated overpressure value is not the result relative to the inflow static pressure; therefore, errors can be introduced when the simulation calculation result based on the inflow static pressure or the real flight test result is compared and analyzed;
2) in the conventional data processing method, the (delta P/P) in the interval 1 is usedMEASURED,0Correcting the whole measuring interval, namely that the pressure difference quantity of the position of the measuring interval and the position of the reference probe is the same under the air wind tunnel condition by default in the method, namely that the pressure distribution in the measuring interval under the air wind tunnel condition is uniform; in actual tests, the pressure distribution in the measurement interval is not necessarily uniform, the pressure distribution is processed according to a traditional data processing method, and the influence of background pressure fluctuation in the sonic boom measurement result is not completely eliminated.
The invention aims to: in order to solve the problem that the conventional method for processing the test data of the wind tunnel for measuring the sonic boom is incomplete in the aspect of eliminating background pressure interference, the method for processing the test data of the wind tunnel for measuring the sonic boom is provided. According to the method, a pressure recovery coefficient and background pressure calibration data under the same wind tunnel body condition and wind tunnel operation parameter are introduced to participate in the processing of the wind tunnel test data of the sonic boom measurement, on one hand, the reference pressure of overpressure value calculation can be normalized into wind tunnel incoming flow static pressure, and on the other hand, the background pressure fluctuation in the wind tunnel test data of the sonic boom measurement can be accurately eliminated point to point. The verification proves that the sound explosion measurement wind tunnel test data determination method can effectively eliminate the problem of incomplete background pressure interference, and has important significance for improving the accuracy and reliability of data determination.
In order to achieve the purpose, the following technical scheme is adopted in the application:
a method for processing test data of a sonic boom measurement wind tunnel comprises the following steps:
A. obtaining a pressure recovery coefficient phi of the probe through theoretical calculation or numerical simulation according to the configuration and the position of the opening of the probe, wherein the pressure recovery coefficient phi is defined as the following formula:
Figure BDA0002264032830000031
wherein, PMEASUREDIs the pressure measurement of the probe, PTRUEIs the true value of pressure;
B. moving the measuring probe along the axial direction of the wind tunnel, carrying out flow field calibration, and obtaining the measured value of the pressure of the measuring probe along the way, which is recorded as P'0i(ii) a The axial position of each measuring point is marked as x0iAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y0；
C. Carrying out model sonic boom measurement wind tunnel test to obtain a measurement probe pressure value of each point along the way, and recording the measurement probe pressure value as P'i(ii) a The axial position of each measuring point is marked as xiAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y, and the corresponding pressure measurement value of the reference probe when the measuring probe is positioned at each measuring point is recorded as P'ri；
D. And (3) obtaining a pressure true value of each measuring point according to the following formula by using a pressure recovery coefficient:
Figure BDA0002264032830000032
Figure BDA0002264032830000033
Figure BDA0002264032830000041
wherein, P0iRefers to a certain measurement position x corrected by a pressure recovery coefficient during a flow field calibration test0iThe corresponding pressure measurement value of the measurement probe, namely the background pressure of the wind tunnel;
Piwhen the wind tunnel test is measured by the sound explosion, a certain measuring position x is corrected by a pressure recovery coefficientiThe pressure measurement value of the corresponding measurement probe;
Priwhen the wind tunnel test is measured by sound explosion, the measuring probe corrected by the pressure recovery coefficient is positioned at a certain measuring position xiWhile, the pressure measurement of the probe, i.e. the reference static pressure, is referenced;
E. calculating the correspondence P of all measurement positions in the whole measurement interval during the flow field calibration test0iIs expressed as P0average；
F. Calculating the position x of each measuring point in the measuring interval during the flow field calibration test0iThe amount of pressure fluctuation DeltaP in comparison with the mean value of the pressure in the measurement interval0i＝(P0i-P0average) (ii) a This value represents each measurement point position x0iThe amount of background pressure fluctuation.
G. (x) obtained during calibration test of flow field0iΔP0i) Interpolation processing is carried out to obtain a measuring position x corresponding to the sonic boom measurement wind tunnel testiIs expressed as Δ P0i-interpolation；
H. Measuring position x obtained during wind tunnel test of sonic boom measurementiCorresponding PiBackground pressure fluctuation quantity delta P of deducting corresponding position0i-interpolationObtaining a corrected pressure measurement value Pi-correction；
I. Certain measuring position x when sound explosion measuring wind tunnel testiWhen the model is positioned outside the sonic boom influence area, the reference static pressure P at the corresponding moment of the position is utilizedriAnd Pi-correctionCalculation (Δ P/P)MEASURED,0The calculation formula is as follows:
Figure BDA0002264032830000042
J. calculating at a certain measuring position xiStatic pressure value P without influence of sonic boomsiThe calculation formula is as follows:
Figure BDA0002264032830000043
K. certain measuring position x when sound explosion measuring wind tunnel testiCorresponding overpressure value when the model is located in the sonic boom influence area
Figure BDA0002264032830000044
Calculated according to the following formula:
Figure BDA0002264032830000045
Figure BDA0002264032830000046
and C, carrying out the flow field calibration test in the step B and the sonic boom measurement wind tunnel test in the step C under the same tunnel body condition and wind tunnel operation parameters. In the technical scheme, the flow field calibration test is required to be carried out under the same tunnel body conditions and the same wind tunnel operation parameters as the sound explosion measurement wind tunnel test in the step B, and the background pressure measurement error caused by different tunnel body conditions introduced in the data processing is avoided by using the previous result instead. The change of the tunnel body condition and the wind tunnel operation parameter can cause the change of the flow field distribution condition, and if the flow field calibration test and the sound explosion measurement wind tunnel test are carried out under different tunnel body conditions and wind tunnel operation parameters, the background pressure correction carried out in the data processing can cause that the background pressure correction is not the background pressure when the sound explosion measurement wind tunnel test is carried out.
And B, the flow field calibration test in the step B is carried out based on the current sonic boom measuring equipment. In the above technical solution, the flow field calibration test in step B is required to be performed based on the current sonic boom measurement device, rather than using results obtained based on other measurement devices, so as to avoid introducing background pressure measurement errors caused by sensitivity differences of different measurement devices in data processing. The conventional supersonic velocity flow field calibration adopts total pressure probe measurement equipment to obtain total pressure after waves are measured, and data processing is carried out to obtain flow field distribution characteristics; the sound explosion measurement wind tunnel test adopts a probe to measure static pressure, different measurement parameters and measurement equipment have difference in the aspect of sensing the pressure distribution sensitivity of the wind tunnel, and the measurement result of one set of equipment is used for correcting the condition that the measurement result of the other set of equipment has different sensitivity to generate data processing errors.
The distance between the axis of the measuring probe in the step B and the wall plate in the vertical direction is consistent with the distance between the axis of the measuring probe in the step C and the wall plate in the vertical direction. That is, in the above-mentioned technical solution, the position of the measuring probe in the height direction must be kept consistent in step B, C, y0Y, to avoid that the difference of background pressure at different height positions affects the experimental data processing results.
And the axial measuring positions of the measuring probes in the steps B and C are kept consistent as much as possible. In the above solution, the axial measurement position of the measurement probe in step B, C should be kept as consistent as possible to reduce the error introduced in the subsequent data interpolation process. Background pressure distribution of the supersonic wind tunnel is greatly influenced by the quality of a molded surface, certain regularity may exist in a small range, and a recyclable law is difficult to find in a large range; therefore, if the axial measurement position deviation of the measurement probe during the flow field calibration test and the sonic boom measurement wind tunnel test is large, a large deviation may exist during the interpolation from the measurement position data of the flow field calibration test to the measurement position of the sonic boom measurement wind tunnel test, thereby affecting the reliability of the background pressure correction.
In the step D, if the configuration of the probe used for the test is consistent with the position of the opening, the pressure recovery coefficient phi is the same value; if the pressure recovery coefficients are not consistent, the pressure recovery coefficients corresponding to the probes are different. In the technical scheme, the pressure recovery coefficient phi in the step D is the same value, and the configuration and the opening position of the probe used in the default test are consistent; if the pressure recovery coefficients are not consistent, the pressure recovery coefficients corresponding to the probes are different.
In the step E, the measurement intervals are all in the same diamond area. In the technical scheme, the measurement intervals are required to be in the same rhombic area in the step E, otherwise, data points in the rhombic area where the model sonic boom influence area is located are selected for calculation during pressure mean calculation, so that the pressure mean calculation is prevented from being influenced by strong pressure mutation caused by strong waves generated by the spray pipe and the test section interface.
In the step G, data interpolation is selected when interpolation processing is performed. In the above technical solution, the interpolation method in step G should select data interpolation to avoid extrapolation of erroneous data.
In the step I, if more than one measuring point is located outside the model sonic boom influence area, the average value of the pressure measuring values of the measuring positions is taken as a calculation parameter. In the above technical solution, if there are more than one measuring points outside the acoustic explosion influence area of the model in step I, the average value of the pressure measurement values at these measuring positions can be taken as a calculation parameter.
In conclusion, the method corrects the influence of the probe configuration on the pressure measurement result, corrects the influence of the uneven background pressure corresponding to the model sonic boom influence area on the pressure measurement result, and improves the accuracy of the sonic boom measurement wind tunnel test result.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
fig. 1 is a schematic diagram of the measurement positions of the model, the measurement probe and the reference probe at a certain measurement position x.
FIG. 2 is a schematic diagram of an unmodified typical sonic boom signature.
Fig. 3 is a schematic view of a wind tunnel test for measuring sonic boom in example 1.
FIG. 4 is a graph showing the results of the flow field calibration test in example 1.
Fig. 5 is a graph of the measured result of the sonic boom signature in example 1.
Fig. 6 is a graph of the background pressure curve (uniform background pressure distribution) of the air tunnel corresponding to the same axial position as that of fig. 5 in example 1.
Fig. 7 is a graph showing the result of the sonic boom signature signal processed according to the conventional data processing method in example 1.
Fig. 8 is a graph of the background pressure curve (uneven background pressure distribution) of the empty wind tunnel corresponding to the same axial position as fig. 5.
Fig. 9 is a graph of a sonic boom signature signal after treatment in example 1 using the method of the present invention.
Fig. 10 shows the pressure fluctuation along the axis in the flow field calibration test.
Figure 11 shows a comparative plot of the correction method.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Example 1
The invention discloses a method for processing test data of a sonic boom measurement wind tunnel.
A. Before the test, according to the configuration and the opening position of the probe, the pressure recovery coefficient phi of the probe is obtained through theoretical calculation or numerical simulation, and the pressure recovery coefficient phi is defined as follows:
Figure BDA0002264032830000061
wherein, PMEASUREDRefers to the pressure measurement of the probe; pTRUEIs the true value of the pressure.
B. As shown in fig. 3, the measurement probe is controlled to move axially along the wind tunnel to perform flow field calibration, and at this time, the model is located at a position of a dotted line in the figure, so that the sonic boom influence generated by the model is propagated downstream, and the measurement of the background pressure of the air wind tunnel is not influenced.
Obtaining a probe pressure measured value along the way by a flow field calibration test and recording the measured value as P'0iAnd the axial position of each measuring point is recorded as x0iAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y0. As shown in fig. 4, x01To x0n1Correspond toThe measuring interval of (2) corresponds to the position of the probe outside the model sonic boom influence area during the sonic boom measuring wind tunnel test, and the n measuring points are 1. x is the number of0n1+1To x0nThe corresponding measuring interval corresponds to the position of the probe outside the model sonic boom influence area during the sonic boom measuring wind tunnel test, and the measuring interval has n-n1 measuring points.
C. As shown in fig. 3, the measurement probe is controlled to move axially along the wind tunnel to carry out the model sonic boom measurement wind tunnel test, and the model is located at the position of the solid line in the figure at the moment. Obtaining a measurement probe pressure value, denoted as P ', at each point along the way'iAnd the axial position of each measuring point is recorded as xiAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y, and y is ensured0The corresponding pressure measurement value of the reference probe when the measurement probe is positioned at each measurement point is recorded as P'ri。
D. The pressure true value of each measuring point is obtained by the following formula:
Figure BDA0002264032830000071
Figure BDA0002264032830000072
Figure BDA0002264032830000073
wherein, P0iRefers to a certain measurement position x corrected by a pressure recovery coefficient during a flow field calibration test0iThe corresponding background pressure; piWhen the wind tunnel test is measured by the sound explosion, a certain measuring position x is corrected by a pressure recovery coefficientiActually measuring static pressure by a corresponding measuring probe; priWhen the wind tunnel test is measured by sound explosion, the measuring probe corrected by the pressure recovery coefficient is positioned at a certain measuring position xiThe pressure measurement of the probe, i.e. the reference static pressure, is referenced.
E. Calculating the correspondence P of all measurement positions in the whole measurement interval during the flow field calibration test0iIs the average value ofP0averageThe calculation formula is as follows:
Figure BDA0002264032830000074
F. calculating the position x of each measuring point in the measuring interval during the flow field calibration test0iAmount of pressure fluctuation Δ P0iThe calculation formula is as follows:
ΔP0i＝(P0i-P0average). This value represents each measurement point position x0iThe amount of background pressure fluctuation.
G. (x) obtained during calibration test of flow field0iΔP0i) Interpolation processing is carried out to obtain a measuring position x corresponding to the sonic boom measurement wind tunnel testiIs expressed as Δ P0i-interpolation。。
H. Measuring position x obtained during wind tunnel test of sonic boom measurementiCorresponding PiBackground pressure fluctuation quantity delta P of deducting corresponding position0i-interpolationCorrected pressure measurement is obtained and is noted as Pi-correctionThe calculation formula is as follows:
Pi-correction＝Pi-ΔP0i-interpolation。
I. certain measuring position x in sound explosion measuring wind tunnel testiWhen the model is positioned outside the sonic boom influence area, the reference static pressure P at the corresponding moment of the position is utilizedriAnd Pi-correctionCalculation (Δ P/P)MEASURED,0The calculation formula is as follows:
Figure BDA0002264032830000081
J. calculating at a certain measuring position xiStatic pressure value P without influence of sonic boomsiThe calculation formula is as follows:
Figure BDA0002264032830000082
K. certain measuring position x in sound explosion measuring wind tunnel testiCorresponding overpressure value when the model is located in the sonic boom influence area
Figure BDA0002264032830000083
Calculated according to the following formula:
Figure BDA0002264032830000084
Figure BDA0002264032830000085
the inventor carries out corresponding verification, and the specific process is as follows.
(1) Theoretical verification
Fig. 5 shows a curve of the measured result of the sonic boom characteristic signal, wherein the abscissa represents the axial position and the ordinate represents the pressure value. The pressure values in interval A represent the reference probe measurement value, the pressure values in interval B represent the measurement value when the measurement probe is outside the model wave system influence region, and the pressure values in interval C represent the measurement value when the measurement probe is in the model wave system influence region.
Fig. 6 shows the background pressure curve (background pressure is uniformly distributed) of the empty wind tunnel corresponding to the same axial position as that in fig. 5, and the coordinate definition is consistent with the interval definition in fig. 1. It can be seen that in fig. 6, the background pressure at the axial positions corresponding to the intervals B and C is uniformly distributed at this time.
Fig. 7 shows the resulting curves of the sonic boom signature after processing according to the conventional data processing method based on the data of fig. 5 and 6. It can be seen that, through data processing, the overvoltage value is zero when the measuring probe is outside the model wave system influence region (region B), and the waveform of the characteristic signal has no large change.
Fig. 8 shows the background pressure curve (uneven background pressure distribution) of the empty wind tunnel corresponding to the same axial position as that of fig. 5. The coordinate definition and the interval definition coincide. It can be seen that the background pressure distribution at the axial positions corresponding to the intervals B and C is not uniform at this time, which is more practical.
Assuming that the pressure values in the intervals a and B in fig. 6 and 8 are the same, the result curve of the sonic boom characteristic signal processed according to the data in fig. 5 and 8 by the conventional data processing method is consistent with that in fig. 7, so that the overpressure value is zero when the measuring probe is outside the influence region of the model wave system (interval B), and the waveform of the characteristic signal has no large change. However, it can be seen that it is impossible to determine whether the overpressure curve given in fig. 7 is a true signature of the sonic boom model because the influence of background pressure fluctuations cannot be eliminated. In short, when the background pressure of the air wind tunnel shown in fig. 6 is uniformly distributed, the data obtained by the conventional correction method is in accordance with the actual situation; when the background pressure distribution of the empty wind tunnel shown in fig. 8 is not uniform, it cannot be determined whether the overpressure curve given in fig. 7 is the true sonic boom characteristic signal of the model.
Fig. 9 shows a graph of the characteristic signature of a sonic boom after processing according to the method described in this patent according to fig. 5 and 8. The coordinate definition and the interval definition are identical to the previous ones. It can be seen that although the original data are consistent, the method can eliminate the interference of background pressure fluctuation on the test result, and can reflect sonic boom characteristics more truly.
(2) Data actual measurement
The results of the wind tunnel flow field calibration and sonic boom measurement tests are given in table 1 below. It should be noted that the wind tunnel flow field calibration result refers to a test result which is developed based on a sonic boom measuring device and is obtained when the model is located at the downstream of the wind tunnel and the wave system of the model does not interfere with the flow field distribution of the upstream empty wind tunnel.
TABLE 1 wind tunnel flow field calibration and sonic boom measurement test results
Figure BDA0002264032830000091
Figure BDA0002264032830000101
Fig. 10 shows the pressure fluctuation along the axis in the flow field calibration test. FIG. 11 is a graph showing a comparative correction method; wherein, the original data, the correction data of the traditional method and the correction data of the invention are respectively given.
As can be seen from fig. 11, compared with the original result, the conventional method basically corrects only the zero point, and the curve is approximately shifted, but the data curve corrected by the method provided by the present application has an obvious difference, especially the peak value variation of the overpressure value corresponding to the vicinity of x ═ 300, compared with the curve of the conventional correction method, the peak value deviation is close to 100% while the zero point is ensured to be consistent, and it can be seen by combining the flow field calibration result curve that the vicinity of x ═ 300 is the position where the background pressure fluctuation is larger, the interference of the background pressure fluctuation is successfully eliminated from the original data by the present invention, and the truth and reliability of the test data are effectively ensured.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.

Claims (9)

1. A sound explosion measurement wind tunnel test data processing method is characterized by comprising the following steps:
A. obtaining a pressure recovery coefficient phi of the probe through theoretical calculation or numerical simulation according to the configuration and the position of the opening of the probe, wherein the pressure recovery coefficient phi is defined as the following formula:
Figure FDA0002781116010000011
wherein, PMEASUREDIs the pressure measurement of the probe, PTRUEIs the true value of pressure;
B. moving the measuring probe along the axial direction of the wind tunnel, carrying out flow field calibration, and obtaining the measured value of the pressure of the measuring probe along the way, which is recorded as P'Oi(ii) a The axial position of each measuring point is marked as xOiAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y0；
C. Wind tunnel test for carrying out model sonic boom measurementChecking to obtain the pressure value of the measuring probe at each point along the way, and recording the pressure value as P'i(ii) a The axial position of each measuring point is marked as xiAnd the distance between the axis of the measuring probe and the wall plate in the vertical direction is recorded as y, and the corresponding pressure measurement value of the reference probe when the measuring probe is positioned at each measuring point is recorded as P'ri；
D. And (3) obtaining a pressure true value of each measuring point according to the following formula by using a pressure recovery coefficient:
Figure FDA0002781116010000012
Figure FDA0002781116010000013
Figure FDA0002781116010000014
wherein, POiRefers to a certain measurement position x corrected by a pressure recovery coefficient during a flow field calibration testOiThe corresponding pressure measurement value of the measurement probe, namely the background pressure of the wind tunnel;
Piwhen the wind tunnel test is measured by the sound explosion, a certain measuring position x is corrected by a pressure recovery coefficientiThe pressure measurement value of the corresponding measurement probe;
Priwhen the wind tunnel test is measured by sound explosion, the measuring probe corrected by the pressure recovery coefficient is positioned at a certain measuring position xiWhile, the pressure measurement of the probe, i.e. the reference static pressure, is referenced;
E. calculating the correspondence P of all measurement positions in the whole measurement interval during the flow field calibration testOiIs expressed as POaverage；
F. Calculating the position x of each measuring point in the measuring interval during the flow field calibration testOiThe amount of pressure fluctuation DeltaP in comparison with the mean value of the pressure in the measurement intervalOi＝(POi-POaverage)；
G. (x) obtained during calibration test of flow fieldOiΔPOi) Interpolation processing is carried out to obtain a measuring position x corresponding to the sonic boom measurement wind tunnel testiIs expressed as Δ POi-interpolation；
H. Measuring position x obtained during wind tunnel test of sonic boom measurementiCorresponding PiBackground pressure fluctuation quantity delta P of deducting corresponding positionOi-interpolationObtaining a corrected pressure measurement value Pi-correction；
I. Certain measuring position x when sound explosion measuring wind tunnel testiWhen the model is positioned outside the sonic boom influence area, the reference static pressure P at the corresponding moment of the position is utilizedriAnd Pi-correctionCalculation (Δ P/P)MEASURED，OThe calculation formula is as follows:
Figure FDA0002781116010000015
J. calculating at a certain measuring position xiStatic pressure value P without influence of sonic boomsiThe calculation formula is as follows:
Figure FDA0002781116010000021
K. certain measuring position x when sound explosion measuring wind tunnel testiCorresponding overpressure value when the model is located in the sonic boom influence area
Figure FDA0002781116010000022
Calculated according to the following formula:
Figure FDA0002781116010000023
Figure FDA0002781116010000024
2. the method according to claim 1, wherein the flow field calibration test in step B and the sonic boom measurement wind tunnel test in step C are performed under the same tunnel body and wind tunnel operating parameter conditions.
3. The method according to claim 1 or 2, wherein the flow field calibration test in step B is performed based on current sonic boom measurement equipment.
4. The method of claim 1, wherein the distance in the vertical direction from the wall plate of the measuring probe axis in step B is the same as the distance in the vertical direction from the wall plate of the measuring probe axis in step C.
5. The method according to claim 1, wherein the axial measuring position of the measuring probe in steps B, C is kept as consistent as possible.
6. The method according to claim 1, wherein in step D, if the configuration of the probe used in the test and the position of the opening are consistent, the pressure recovery coefficient Φ is the same value; if the pressure recovery coefficients are not consistent, the pressure recovery coefficients corresponding to the probes are different.
7. The method according to claim 1, wherein in step E, the measurement intervals are all within the same diamond-shaped area.
8. The method according to claim 1, wherein in the step G, data interpolation is selected when the interpolation processing is performed.
9. The method according to claim 1, wherein in step I, if there are more than one measuring points outside the sonic boom influence region of the model, the average of the pressure measurements at these measuring positions is taken as the calculation parameter.
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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CN117760681B (en) * 2024-02-22 2024-05-31 中国空气动力研究与发展中心高速空气动力研究所 Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5534995A (en) * 1995-02-14 1996-07-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Schlieren system and method for moving objects
CN206740359U (en) * 2016-12-08 2017-12-12 中国航空工业集团公司沈阳空气动力研究所 A kind of supersonic aircraft sonic boom token test measurement apparatus
CN109186934A (en) * 2018-11-15 2019-01-11 中国航空工业集团公司沈阳空气动力研究所 A kind of space near field sonic boom feature high precision measuring device
CN110132528A (en) * 2019-06-27 2019-08-16 中国空气动力研究与发展中心高速空气动力研究所 It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method
CN110220665A (en) * 2019-06-24 2019-09-10 中国空气动力研究与发展中心高速空气动力研究所 A kind of method for security protection for temporarily rushing formula supersonic wind tunnel lower range and surveying pressure scanning valve

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106338399B (en) * 2016-08-16 2019-03-08 中国航空工业集团公司沈阳发动机设计研究所 A kind of calculation method across the total static probe measurement true value of supersonic speed
CN108036917B (en) * 2017-12-15 2019-09-06 中国航空工业集团公司金城南京机电液压工程研究中心 A kind of ram-air turbine wind tunnel test test method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5534995A (en) * 1995-02-14 1996-07-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Schlieren system and method for moving objects
CN206740359U (en) * 2016-12-08 2017-12-12 中国航空工业集团公司沈阳空气动力研究所 A kind of supersonic aircraft sonic boom token test measurement apparatus
CN109186934A (en) * 2018-11-15 2019-01-11 中国航空工业集团公司沈阳空气动力研究所 A kind of space near field sonic boom feature high precision measuring device
CN110220665A (en) * 2019-06-24 2019-09-10 中国空气动力研究与发展中心高速空气动力研究所 A kind of method for security protection for temporarily rushing formula supersonic wind tunnel lower range and surveying pressure scanning valve
CN110132528A (en) * 2019-06-27 2019-08-16 中国空气动力研究与发展中心高速空气动力研究所 It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
An Analysis of Measured Sonic-Boom Pressure Signatures From a Langley Wind-Tunnel Model of a Supersonic-Cruise Business Jet Concept;Robert J. Mack;《NASA Center for AeroSpace Information》;20031231;第1-19页 *
典型低音爆构型的近场音爆计算研究;徐悦;《航空科学技术》;20160115;第27卷(第7期);第12-16页 *
声爆近场压力测量风洞试验技术研究进展;刘中臣;《空气动力学学报》;20190831;第37卷(第4期);第636-644页 *

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