CN114323536B - Interpolation method for improving measurement accuracy of five-hole probe - Google Patents
Interpolation method for improving measurement accuracy of five-hole probe Download PDFInfo
- Publication number
- CN114323536B CN114323536B CN202111654562.4A CN202111654562A CN114323536B CN 114323536 B CN114323536 B CN 114323536B CN 202111654562 A CN202111654562 A CN 202111654562A CN 114323536 B CN114323536 B CN 114323536B
- Authority
- CN
- China
- Prior art keywords
- calibration
- wind tunnel
- mach number
- interpolation
- calculating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses an interpolation method for improving measurement accuracy of a five-hole probe, which comprises the steps of calibrating the five-hole probe in a calibration wind tunnel to obtain calibration coefficients corresponding to different incoming flow Mach numbers, and constructing a calibration wind tunnel data set, wherein the calibration wind tunnel data set comprises pressure readings of five pressure sensing holes, total incoming flow pressure, incoming flow static pressure, pitch angle, yaw angle and calibration coefficients in the calibration wind tunnel; correcting and calibrating dead pixels in the wind tunnel data set; constructing a calibration wind tunnel data matrix according to the corrected calibration wind tunnel data set, wherein the calibration wind tunnel data matrix comprises Mach numbers, pitch angles, yaw angles and calibration coefficients; and obtaining the outlet Mach number or the inlet Mach number of the test flow field, calculating the difference value between the outlet Mach number or the inlet Mach number and the incoming flow Mach number in the calibration wind tunnel, and executing a two-dimensional interpolation method when the difference value is smaller than a threshold value, otherwise, executing a three-dimensional interpolation method. The invention can avoid accumulated errors, improve measurement accuracy and facilitate the programmed processing of data.
Description
Technical Field
The invention relates to the technical field of engineering measurement, in particular to an interpolation method for improving measurement accuracy of a five-hole probe.
Background
The five-hole probe is widely applied to measurement of a three-dimensional flow field due to the advantages of simple principle, low cost, low maintenance cost and the like. The five-hole probe shown in fig. 2 is composed of two pairs of vertically arranged holes including 1 hole and 3 holes, 4 holes and 5 holes, and a central hole (2 holes), and a cartesian coordinate system is established based on the holes, thereby realizing three-dimensional decomposition of speed.
The five-hole probe is generally calibrated and then used, namely, a calibration coefficient is firstly obtained in a calibration wind tunnel, and when an unknown flow field is measured, real data of the flow field is obtained through interpolation of calibration data. By means of computer programming technology, a large amount of calibration and test data can be processed quickly, and the non-opposite measurement method is widely applied. Pressure readings (P, -, P) using five pressure sensing holes in non-subtended measurement 5 ) And calibrating the total pressure of the incoming flow (P) t ) Static pressure of incoming flow (P) S ) 4 calibration coefficients (k α ,K β 、Cpt、Crs)。
Theory and experiment show that the calibration coefficient is uniquely determined by the flow angle within a certain range. Therefore, the relative angle of the incoming flow and the probe head is sequentially changed according to the fixed direction during calibration, and the corresponding calibration coefficient is recorded.
The relative position of the air flow to the probe is defined by two angles:
beta angle-the angle between the air flow and the X-Z plane, called pitch angle;
angle a-the angle between the projection of the air flow on the X-Z plane and the Z axis, called yaw angle.
After calibration, an angular coefficient network shown in fig. 3, a total pressure coefficient curve cluster shown in fig. 4 and a hydrostatic coefficient curve cluster shown in fig. 5 can be obtained.
Currently, a method generally adopted in measurement is to first calculate two angle coefficients (K based on 5 measured pressure values of a five-hole probe α And K β ) And obtaining two direction angles through interpolation of an angle coefficient network, obtaining corresponding coefficients according to the total pressure coefficient and static pressure coefficient curve clusters through interpolation of the direction angles, and further reversely calculating the total pressure, the static pressure and the speed of a flow field. Typically, the velocity magnitude is obtained according to the Bernoulli equation, and the presence of the direction angle enables it to be resolved into the coordinate system shown in FIG. 2.
The interpolation method of the probe can be seen in the text of application of non-opposite method and mixed programming in the measurement of the cascade flow field. In general, the interpolation method of the five-hole probe is local, and it should be noted that the local interpolation method is simple in principle and high in efficiency, but does not fully consider the influence of global data, and the calibration data of the five-hole probe is generally calculated amount which can be born by the global interpolation method, so that a two-dimensional global interpolation method is proposed. It should also be noted that the method generally used for five-hole probes is obtained by interpolating twice for the total pressure and the static pressure, and in order to reduce the error, the new two-dimensional global interpolation method directly takes the angle coefficient as an independent variable, and interpolates the total pressure coefficient and the static pressure coefficient instead of calculating the two direction angles. The set of calibration data is obtained under fixed incoming stream Mach number conditions as shown in FIGS. 3-5. In measuring the cascade exit flow field parameters, a set of calibration data similar to the incoming flow Mach number is typically used for calculation. Because of the influence of compressibility, there are differences in calibration data under different high-speed conditions, and at the same time, there are also differences in the secondary flow at the cascade outlet and the high-speed flow in the main flow region, which all result in inaccurate calculation using the cascade inlet Mach number calibration data. Therefore, in the processing of the test result, the incoming flow Mach number is also interpolated, so that the measurement accuracy of the five-hole probe can be improved.
The patent 'a five-hole probe data processing method' (application number 201610304865.6) carries out similar processing, but still adopts a twice interpolation mode in the process of solving the total pressure and the static pressure.
In order to reduce errors, the Mach number and the two angle coefficients are used as independent variables, three-dimensional interpolation is carried out on the direction angle, the total pressure coefficient and the static pressure coefficient respectively, and continuous iteration is carried out on the basis of the Mach number, so that a measurement result in control accuracy is obtained. The two-dimensional interpolation calculation based on the double-tone and curved surface interpolation algorithm of the green function can realize overall two-dimensional interpolation calculation, can minimize the curvature at the interpolation point, has the advantages of high precision and more flexibility, but is not suitable for being used in the interpolation problem with more than three dimensions. The natural neighborhood method based on Voronoi (taylor) subdivision is a robust local interpolation algorithm with linear accuracy, and the weighting coefficient depends on the size of the area formed by surrounding scattered points and interpolation points. When the interpolation point approaches the region boundary, the problem of larger error caused by the region subdivision problem may occur in the natural neighborhood method. Thus, the new interpolation method will achieve satisfactory results: when the interpolation Mach number is close to the calibration Mach number, a double-tone and curved surface interpolation algorithm is used, and when the difference between the two is large, a three-dimensional natural neighborhood method is used.
Due to the pulsation of the air flow in the calibration wind tunnel and other disturbances in the measurement process, bad spots inevitably appear in the calibration data. The interpolation method has strong dependence on the original data, the existence of the dead pixels can cause larger measurement errors, and the work of setting the dead pixel correction before interpolation calculation is necessary.
The invention uses the law that the calibration coefficient changes along with the angle, finds out the data point with larger deviation by curve fitting and Laida criterion of data point deviation, further obtains new data point by interpolation method, and ensures the rationality of the new data by the deviation verification again.
Disclosure of Invention
The invention provides an interpolation method for improving the measurement accuracy of a five-hole probe, so as to overcome the technical problems.
An interpolation method for improving the measurement precision of a five-hole probe is characterized by comprising the following steps of,
and 6, executing a three-dimensional interpolation method when the difference value is larger than the threshold value.
Preferably, the correcting and calibrating the dead pixel in the wind tunnel data set specifically comprises,
2a, sequentially selecting a yaw angle and a calibration coefficient corresponding to the incoming flow Mach number and the pitch angle, performing curve fitting on the yaw angle and the calibration coefficient, wherein independent variables of the curve fitting are yaw angles, the calibration coefficient is taken as an ordinate respectively, a fitting curve is obtained, fitting values of the calibration coefficient are obtained according to the fitting curve respectively, and the deviation between the calibration coefficient and the fitting values thereof is calculated;
and 2b, judging the Laida criterion for the deviation, if the deviation is a dead pixel, deleting the yaw angle and the calibration coefficient, calculating the correction values of the yaw angle and the calibration coefficient through a cubic spline interpolation method, re-executing the step 2a, and when the dead pixel is an endpoint of a fitting curve, calculating the correction values of the yaw angle and the calibration coefficient through an extrapolation method, and re-executing the step 2a.
Preferably, the two-dimensional interpolation method is performed, specifically including,
5a, calculating to obtain an angle coefficient in the calibration coefficient according to the pressure value of the five-hole probe;
5b, selecting a calibration wind tunnel data matrix according to the outlet Mach number or the inlet Mach number of the test flow field;
5c, constructing an interpolation point according to the angle coefficient, wherein the interpolation point comprises a pitch angle, a yaw angle and a calibration coefficient, the pitch angle and the yaw angle are manufactured in a radian mode, calculating the value of each variable in the interpolation point according to a selected calibration wind tunnel data matrix by a double-harmonic curved surface interpolation method, and obtaining the total pressure, the static pressure and the Mach number of the test flow field by reverse calculation;
and 5d, calculating the difference value between the Mach number obtained by the step 5c and the Mach number of the incoming flow in the calibrated wind tunnel, re-entering the step 5b by taking the Mach number obtained by the step 5c as the Mach number of the test flow field when the difference value is larger than a threshold value, calculating the absolute speed of the test flow field according to the total temperature of the incoming flow, the Mach number and the isentropic flow process when the difference value is smaller than the threshold value, and carrying out three-dimensional decomposition.
Preferably, the method for performing three-dimensional interpolation, in particular,
6a, performing Voronoi subdivision on the calibrated wind tunnel data matrix, and constructing interpolation points, wherein the interpolation points comprise Mach numbers, pitch angles, yaw angles and calibration coefficients, and the acquired inlet Mach numbers or outlet Mach numbers of the test flow fields are used as Mach numbers of the interpolation points;
6b, calculating the values of variables in the interpolation points according to Mach numbers of the interpolation points, angle coefficients in calibration coefficients, a calibration wind tunnel data matrix and a natural neighborhood method based on Voronoi subdivision, and obtaining total pressure, static pressure and Mach numbers of the test flow field through reverse calculation;
and 6c, calculating the difference between the Mach number of the interpolation point and the outlet Mach number or the inlet Mach number of the test flow field, if the difference exceeds the difference, re-entering the test flow field 6a for execution, otherwise, calculating the absolute speed of the test flow field according to the total temperature, the Mach number and the isentropic flow process of the incoming flow, and carrying out three-dimensional decomposition.
The invention provides an interpolation method for improving the measurement precision of a five-hole probe, which changes the two-step interpolation solving process of total pressure and static pressure into one-step interpolation solving by establishing a numerical matrix of calibration coefficients, avoids accumulated errors, improves the measurement precision and is more convenient for the programmed processing of data; in order to reduce measurement errors, dead point correction processing is carried out on data in a calibration file, so that the data for interpolation calculation is more reasonable; in order to compensate for the short plates between interpolation methods, a two-dimensional/three-dimensional combination method is adopted, the two-dimensional interpolation method has higher precision, and the three-dimensional method has better stability; the result is subjected to iterative processing by taking Mach number as a control means, and compared with the traditional method, the error is smaller.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments or the description of the prior art will be briefly described below, it will be obvious that the drawings in the following description are some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort to a person skilled in the art.
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a three-dimensional exploded view of a five-hole probe of the present invention;
FIG. 3 is a graph of an angle coefficient network of the present invention;
FIG. 4 is a graph of total pressure coefficient curve of the present invention;
FIG. 5 is a graph of the hydrostatic coefficient curve of the present invention;
FIG. 6 is an alpha error plot of a conventional method of the present invention and a method of the present invention;
FIG. 7 is a graph of the beta error of the conventional method of the present invention and the method of the present invention;
FIG. 8 is a graph of total pressure error for the conventional method of the present invention and the method of the present invention;
FIG. 9 is a graph of static pressure error for a conventional method of the present invention and a method of the present invention;
fig. 10 is a map of the Ma error of the conventional method of the present invention and the method of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
FIG. 1 is a flowchart of the method of the present invention, as shown in FIG. 1, the method of the present embodiment may include:
an interpolation method for improving the measurement precision of a five-hole probe comprises the following steps,
2a, sequentially selecting a yaw angle and a calibration coefficient corresponding to an incoming flow Mach number and a pitch angle, and performing curve fitting on the yaw angle and the calibration coefficient, wherein the independent variable of the curve fitting is the yaw angle, and the calibration coefficient is taken as an ordinate to obtain a simulationFitting curves, i.e. fitting alpha-K α 、α-K β G-Cpt and alpha-Cps curves, wherein the alpha angle is a yaw angle, fitting values of the calibration coefficients are obtained according to the fitting curves, and deviation between the calibration coefficients and the fitting values is calculated;
2b, judging the Laida criterion of the deviation, if the deviation is a dead pixel, deleting the yaw angle and the calibration coefficient, calculating the correction values of the yaw angle and the calibration coefficient through a cubic spline interpolation method, re-executing the step 2a, and when the dead pixel is an endpoint of a fitting curve, calculating the correction values of the yaw angle and the calibration coefficient through an extrapolation method, and re-executing the step 2a;
the extrapolation method is to select two points adjacent to a dead pixel, calculate the slope k between the two selected points, set the cycle number as n, calculate the slope k 'of the endpoint and the adjacent point according to the formula (6), and obtain the correction value of the yaw angle and the calibration coefficient through the adjacent point and the slope k';
5a, calculating an angle coefficient in the calibration coefficient according to the pressure value of the five-hole probe, namely calculating a corresponding K' α And K' β ；
5b, selecting a calibration wind tunnel data matrix according to the outlet Mach number or the inlet Mach number of the test flow field;
5c, constructing interpolation points according to the angle coefficients, wherein the interpolation points comprise pitch angles, yaw angles and calibration coefficients, the pitch angles and the yaw angles are radian-manufactured, and calculating the values of variables in the interpolation points according to the selected calibration wind tunnel data matrix by a bi-level curved surface interpolation method, namely, recording the coordinates of the interpolation points as X= (K '' α ，K′ β ) The coordinates of the marked point are
Where N is the number of data points, and the value of the index point is w j Calculating the value of the interpolation point according to the hyperbolic and curved surface interpolation method, wherein the expression form of the Grignard spline interpolation function w (X) adopted in the hyperbolic and curved surface interpolation method is as follows
Wherein phi is m ＝|X| 2 (ln|X|-1)，α j By->
Solving for [ a ', beta', cpt ', cps ]']Then the equation is sequentially solved to obtain;
the total pressure, the static pressure and the Mach number of the test flow field are obtained through reverse calculation, namely, according to Cpt 'and Cps', a coefficient equation is reversely solved, the corresponding total pressure and static pressure are obtained, and the Mach number is further solved;
5d, calculating the difference value between the Mach number obtained by the step 5c and the incoming flow Mach number in the calibrated wind tunnel, re-entering the step 5b for execution when the difference value is larger than a threshold value, calculating the absolute speed of a test flow field according to the total incoming flow temperature, the Mach number and the isentropic flow process when the difference value is smaller than the threshold value, and then carrying out three-dimensional decomposition on the test flow field according to alpha ', beta' obtained by interpolation to obtain the coordinate shown in the figure 2;
6a, performing Voronoi subdivision on the calibration wind tunnel data matrix, namely, performing Voronoi subdivision on the calibration wind tunnel data matrix [ Ma, K ] α ，K β ]Voronoi subdivision is performed, and [ alpha, beta, cpt, cps ] of the interpolation points are interpolated]Becomes the attribute value thereof, and is denoted by z;
constructing an interpolation point, wherein the interpolation point comprises Mach numbers, pitch angles, yaw angles and calibration coefficients, and the acquired inlet Mach numbers or outlet Mach numbers of the test flow fields are used as Mach numbers of the interpolation point;
6b, calculating the value of each variable in the interpolation point according to Mach number of the interpolation point, angle coefficient in the calibration coefficient, calibration wind tunnel data matrix and natural neighborhood method based on Voronoi subdivision, namely recording the coordinate of the interpolation point as X= (Ma ', K ' ' α ，K′ β ) The interpolation point is 'invaded' into Voronoi subdivision space, and the neighborhood T is found i (i represents the number of the neighborhood), the attribute values [ alpha ', beta ', cpt ', cps ' of the interpolation points ']Can be according to
Solving, wherein M is the number of the neighborhoods; w (w) i (x) For the weighting factor>
Wherein h is i (x) D (x, x) is the ratio of the interpolation point to the neighborhood space i ) Is the Euclidean distance; g i (x) Representing derivative +.>
According to Cpt 'and Cps' reversely calculating to obtain the total pressure, static pressure and Mach number of the test flow field;
and 6c, calculating the difference between the Mach number of the interpolation point and the outlet Mach number or the inlet Mach number of the test flow field, and if the difference exceeds the difference, re-entering the test flow field to be executed in 6a, otherwise, calculating the absolute speed of the test flow field according to the total temperature, the Mach number and the isentropic flow process of the incoming flow, and then carrying out three-dimensional decomposition on the test flow field according to alpha ', beta' obtained by interpolation to obtain the coordinate shown in figure 2.
Given calibration data with incoming stream Mach numbers of 0.3, 0.5 and 0.7, comparing flow field results of working conditions with incoming stream Mach numbers of 0.3-0.7 with the conventional method, the interpolation method provided by the invention is found to have smaller errors than the conventional method, fig. 6 is an alpha error map of the conventional method and the method, fig. 7 is a beta error map of the conventional method and the method, fig. 8 is a total pressure error map of the conventional method and the method, fig. 9 is a static pressure error map of the conventional method and the method, and fig. 10 is a Ma error map of the conventional method and the method.
The whole beneficial effects are that:
by establishing a numerical matrix of calibration coefficients, the two-step interpolation solving process of total pressure and static pressure is changed into one-step interpolation solving, so that accumulated errors are avoided, the measurement precision is improved, and the programmed processing of data is facilitated; in order to reduce measurement errors, dead point correction processing is carried out on data in a calibration file, so that the data for interpolation calculation is more reasonable; in order to compensate for the short plates between interpolation methods, a two-dimensional/three-dimensional combination method is adopted, the two-dimensional interpolation method has higher precision, and the three-dimensional method has better stability; the result is subjected to iterative processing by taking Mach number as a control means, and compared with the traditional method, the error is smaller.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (4)
1. An interpolation method for improving the measurement precision of a five-hole probe is characterized by comprising the following steps of,
step 1, calibrating a five-hole probe in a calibration wind tunnel to obtain calibration coefficients corresponding to different incoming flow Mach numbers, and constructing a calibration wind tunnel data set, wherein the calibration wind tunnel data set comprises pressure readings of five pressure sensing holes, incoming flow total pressure, incoming flow static pressure, pitch angle, yaw angle and calibration coefficients in the calibration wind tunnel;
step 2, correcting dead pixels in the calibrated wind tunnel data set;
step 3, constructing a calibration wind tunnel data matrix according to the corrected calibration wind tunnel data set, wherein the calibration wind tunnel data matrix comprises Mach numbers, pitch angles, yaw angles and calibration coefficients, and the pitch angles and the yaw angles are radian systems;
step 4, obtaining the outlet Mach number or the inlet Mach number of the test flow field, and calculating the difference value between the outlet Mach number or the inlet Mach number and the incoming flow Mach number in the calibration wind tunnel;
step 5, when the difference value is smaller than the threshold value, executing a two-dimensional interpolation method;
and 6, executing a three-dimensional interpolation method when the difference value is larger than the threshold value.
2. The interpolation method for improving the measurement accuracy of the five-hole probe according to claim 1, wherein the correction and calibration of dead pixels in the wind tunnel dataset comprises,
2a, sequentially selecting a yaw angle and a calibration coefficient corresponding to the incoming flow Mach number and the pitch angle, performing curve fitting on the yaw angle and the calibration coefficient, wherein independent variables of the curve fitting are yaw angles, the calibration coefficient is taken as an ordinate respectively, a fitting curve is obtained, fitting values of the calibration coefficient are obtained according to the fitting curve respectively, and the deviation between the calibration coefficient and the fitting values thereof is calculated;
and 2b, judging the Laida criterion for the deviation, if the deviation is a dead pixel, deleting the yaw angle and the calibration coefficient, calculating the correction values of the yaw angle and the calibration coefficient through a cubic spline interpolation method, re-executing the step 2a, and when the dead pixel is an endpoint of a fitting curve, calculating the correction values of the yaw angle and the calibration coefficient through an extrapolation method, and re-executing the step 2a.
3. An interpolation method for improving measurement accuracy of a five-hole probe according to claim 1, wherein the performing of the two-dimensional interpolation method comprises,
5a, calculating to obtain an angle coefficient in the calibration coefficient according to the pressure value of the five-hole probe;
5b, selecting a calibration wind tunnel data matrix according to the outlet Mach number or the inlet Mach number of the test flow field;
5c, constructing an interpolation point according to the angle coefficient, wherein the interpolation point comprises a pitch angle, a yaw angle and a calibration coefficient, the pitch angle and the yaw angle are manufactured in a radian mode, calculating the value of each variable in the interpolation point according to a selected calibration wind tunnel data matrix by a double-harmonic curved surface interpolation method, and obtaining the total pressure, the static pressure and the Mach number of the test flow field by reverse calculation;
and 5d, calculating the difference value between the Mach number obtained by the step 5c and the Mach number of the incoming flow in the calibrated wind tunnel, re-entering the step 5b by taking the Mach number obtained by the step 5c as the Mach number of the test flow field when the difference value is larger than a threshold value, calculating the absolute speed of the test flow field according to the total temperature of the incoming flow, the Mach number and the isentropic flow process when the difference value is smaller than the threshold value, and carrying out three-dimensional decomposition.
4. The interpolation method for improving the measurement accuracy of a five-hole probe according to claim 1, wherein the performing of the three-dimensional interpolation method comprises,
6a, performing Voronoi subdivision on the calibrated wind tunnel data matrix, and constructing interpolation points, wherein the interpolation points comprise Mach numbers, pitch angles, yaw angles and calibration coefficients, and the acquired inlet Mach numbers or outlet Mach numbers of the test flow fields are used as Mach numbers of the interpolation points;
6b, calculating the values of variables in the interpolation points according to Mach numbers of the interpolation points, angle coefficients in calibration coefficients, a calibration wind tunnel data matrix and a natural neighborhood method based on Voronoi subdivision, and obtaining total pressure, static pressure and Mach numbers of the test flow field through reverse calculation;
and 6c, calculating the difference between the Mach number of the interpolation point and the outlet Mach number or the inlet Mach number of the test flow field, if the difference exceeds the difference, re-entering the test flow field 6a for execution, otherwise, calculating the absolute speed of the test flow field according to the total temperature, the Mach number and the isentropic flow process of the incoming flow, and carrying out three-dimensional decomposition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111654562.4A CN114323536B (en) | 2021-12-30 | 2021-12-30 | Interpolation method for improving measurement accuracy of five-hole probe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111654562.4A CN114323536B (en) | 2021-12-30 | 2021-12-30 | Interpolation method for improving measurement accuracy of five-hole probe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114323536A CN114323536A (en) | 2022-04-12 |
| CN114323536B true CN114323536B (en) | 2023-05-26 |
Family
ID=81019541
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111654562.4A Active CN114323536B (en) | 2021-12-30 | 2021-12-30 | Interpolation method for improving measurement accuracy of five-hole probe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114323536B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115452313B (en) * | 2022-11-14 | 2023-03-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for quickly calibrating angular sensitivity of probe in sonic explosion test |
| CN116007884B (en) * | 2023-03-21 | 2023-05-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Five-hole probe spherical coordinate data processing method considering compressibility |
| CN116558769B (en) * | 2023-07-12 | 2023-09-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Five-hole probe calibration data application method considering compressibility |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106096223A (en) * | 2016-05-10 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of five-hole probe data processing method |
| CN110514391A (en) * | 2019-08-12 | 2019-11-29 | 北京航空航天大学 | A kind of five pore pressure force probes measurement three-dimensional flow field uncertainty evaluation method |
| CN111896211A (en) * | 2020-07-29 | 2020-11-06 | 大连海事大学 | Partition interpolation method for five-hole probe under large incoming flow angle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4100515B2 (en) * | 2004-09-17 | 2008-06-11 | 独立行政法人 宇宙航空研究開発機構 | High-speed, wide-range flight speed vector measurement probe and measurement system |
| US9864099B2 (en) * | 2012-11-20 | 2018-01-09 | Kyungpook National University Industry-Academic Cooperation | Apparatus and method for calculating wind load |
-
2021
- 2021-12-30 CN CN202111654562.4A patent/CN114323536B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106096223A (en) * | 2016-05-10 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of five-hole probe data processing method |
| CN110514391A (en) * | 2019-08-12 | 2019-11-29 | 北京航空航天大学 | A kind of five pore pressure force probes measurement three-dimensional flow field uncertainty evaluation method |
| CN111896211A (en) * | 2020-07-29 | 2020-11-06 | 大连海事大学 | Partition interpolation method for five-hole probe under large incoming flow angle |
Non-Patent Citations (2)
| Title |
|---|
| 亚声速条件下五孔探针非线性插值计算方法研究;史远鹏;王佳璐;陆华伟;孔晓治;王宇;;风机技术(04);P39-48 * |
| 基于变马赫数的五孔探针三维插值方法;陆华伟;路子平;平梓昕;郭爽;;南京航空航天大学学报(04);P96-103 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114323536A (en) | 2022-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114323536B (en) | Interpolation method for improving measurement accuracy of five-hole probe | |
| CN106096223B (en) | Five-hole probe data processing method | |
| CN112396690B (en) | Curved surface high-precision reconstruction method based on improved centripetal parameterization method | |
| US7228254B2 (en) | Shape model generation method and shape model generation system | |
| CN110060342B (en) | Three-dimensional curved surface fitting method | |
| CN108362911B (en) | Flow velocity meter calibration method based on least square method and interpolation method | |
| CN107526875A (en) | A kind of aerial blade type face mismachining tolerance method for visualizing | |
| CN112381862B (en) | Full-automatic registration method and device for CAD (computer-aided design) model and triangular mesh | |
| Feng et al. | An adaptive sampling method for accurate measurement of aeroengine blades | |
| CN112396567B (en) | Scattered point cloud denoising method based on normal correction and position filtering two-step method | |
| CN112033338B (en) | Blade curved surface contact type scanning measurement probe radius surface compensation method | |
| Rouhani et al. | Implicit polynomial representation through a fast fitting error estimation | |
| CN115358026A (en) | Five-hole probe data processing method based on multivariate linear regression and surface fitting | |
| Liu et al. | High precision measurement of blade profile curve using iterative normal vector approximation | |
| CN117874900B (en) | House construction engineering supervision method based on BIM technology | |
| CN111260776A (en) | Three-dimensional shape reconstruction method for adaptive normal analysis | |
| Bauer et al. | Generating parametric models of tubes from laser scans | |
| CN111487440A (en) | Calibration method of five-hole probe | |
| CN109375160B (en) | Angle measurement error estimation method in pure-azimuth passive positioning | |
| JP4981313B2 (en) | Three-dimensional shape processing apparatus, curved surface creation program, and curved surface creation method | |
| CN108595373B (en) | Uncontrolled DEM registration method | |
| CN114117315B (en) | Straightness estimation method and straightness estimation system based on minimum inclusion area | |
| CN115408960A (en) | Method for parametrically processing five-hole probe data | |
| CN106570915B (en) | Method for extracting trunk diameter of full-convex closed continuous curve based on point cloud data | |
| CN108917632B (en) | High-efficiency high-precision digital image correlation displacement post-processing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |