CN112556971A - Method for measuring length of interference zone of transonic wind tunnel support system - Google Patents
Method for measuring length of interference zone of transonic wind tunnel support system Download PDFInfo
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- CN112556971A CN112556971A CN202011514334.2A CN202011514334A CN112556971A CN 112556971 A CN112556971 A CN 112556971A CN 202011514334 A CN202011514334 A CN 202011514334A CN 112556971 A CN112556971 A CN 112556971A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a method for measuring the length of an interference area of a transonic wind tunnel support system. According to the measuring method, the axial static pressure detecting tube is used for measuring the Mach number distribution of the central axis of the transonic wind tunnel test section, the Mach number distribution is compared with a flow correction result, the Mach number deviation of the same position is taken as the reference, when the Mach number deviation of the same position exceeds 0.005, the position is considered to be interfered by a supporting system, the distance S from the position to the outlet of the transonic wind tunnel test section is measured, and S is the length of an interference area. The measuring device used by the measuring method is simple and reliable in structure, convenient and fast in operation method, good in repeatability, strong in adaptability and high in application value, and has important significance in improving the transonic wind tunnel test quality and optimizing design of the model supporting mechanism.
Description
Technical Field
The invention belongs to the technical field of transonic wind tunnel tests, and particularly relates to a method for measuring the length of an interference area of a transonic wind tunnel support system.
Background
The model in the transonic wind tunnel test is arranged on a middle support of the transonic wind tunnel through a supporting system, different supporting systems are selected according to task requirements during the wind tunnel test, a direct head or a double-rotating-shaft system is generally selected for model supporting in a conventional force and pressure measuring test, and then the change of the model posture is realized by combining an angle-of-attack system of the transonic wind tunnel, so that aerodynamic force measurement or pressure measurement of the model is completed.
Through the arrangement, induction and analysis of test data in the past year, the support system can be found to have certain influence on the transonic wind tunnel test data. However, due to the lack of research on the interference of the support system, the interference of the support system on the transonic wind tunnel test data cannot be accurately determined, and when the test data is subjected to support interference correction at present, only simple correction can be performed on the mach number distribution of the transonic wind tunnel core flow field obtained by flow field calibration.
The length of an interference area and the length of the interference area are two core basic concepts for correction, and the interference area refers to an area where a core flow field generates flow field distortion due to the existence of a supporting system. The length of the interference zone refers to the distance from the region of the core flow field where distortion beyond a specified range begins to the outlet of the test section.
At present, a method for measuring the length of an interference area of a transonic wind tunnel supporting system needs to be developed urgently, the interference degree of the supporting system to a core flow field is further accurately measured by quantifying the length of the interference area of the supporting system, the interference area of the supporting system is avoided as much as possible when a wind tunnel test model is installed, and the transonic wind tunnel test data quality is improved.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for measuring the length of an interference area of a transonic wind tunnel support system.
The measuring device used in the method for measuring the length of the interference zone of the transonic wind tunnel support system is an axial static pressure detecting tube; the head of the axial static pressure detection tube is a conical rotation body, a generatrix of the conical rotation body is an arc curve, the length of the conical rotation body is L, the diameter of the bottom of the conical rotation body is D, and the slenderness ratio of the head is L, D is (7-8): 1; the middle section of the axial static pressure detection tube is a cylindrical section, and the diameter of the cylindrical section is D; the rear section of the axial static pressure detection tube is a cylindrical measurement section, the diameter of the cylindrical measurement section is D, and static pressure measurement points which are linearly arranged are arranged in the cylindrical measurement section along the axis direction; the method is characterized by comprising the following steps:
a. installing an axial detection bent frame on a middle support of the transonic wind tunnel, starting the transonic wind tunnel under the condition that the Mach number Ma is 0, moving the axial detection bent frame according to a preset path, changing a measurement position until the measurement is completed, closing the transonic wind tunnel, and obtaining the Mach number distribution of a transonic wind tunnel core flow field of the Mach number Ma0 after data processing to obtain a transonic wind tunnel flow correction result;
b. the method comprises the following steps of (1) removing an axial detection bent, installing a supporting mechanism, and installing an axial static pressure detection pipe on the supporting mechanism, wherein the axial static pressure detection pipe is positioned on a central axis of a transonic wind tunnel test section, and the head of the axial static pressure detection pipe faces to an incoming flow of a wind tunnel;
c. starting the transonic wind tunnel under the Mach number Ma0, measuring the static pressure distribution of the central axis of the transonic wind tunnel test section by an axial static pressure detecting tube, and closing the transonic wind tunnel;
d. carrying out data processing to obtain Mach number distribution of a central axis of the transonic wind tunnel test section with the Mach number Ma being Ma 0;
e. c, comparing the Mach number distribution of the central axis of the transonic wind tunnel test section obtained in the step d with the Mach number distribution of the transonic wind tunnel core flow field obtained in the step a, and finishing the measurement work of the axial static pressure probe tube if the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005; otherwise, moving the middle support towards the wind tunnel incoming flow direction through the transonic wind tunnel control system, and measuring the Mach number distribution of the central axis of the transonic wind tunnel test section again until the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005;
f. recording a first position where Mach number deviation of a corresponding measuring point is greater than or equal to 0.005, and calculating the distance A from the first position to an outlet of a transonic wind tunnel test section, wherein A is the length of an interference area with Mach number Ma being Ma 0;
g. and (f) repeating the steps a to f to obtain the lengths of the interference areas under all Mach numbers of the transonic wind tunnel.
The measuring device used by the method for measuring the length of the interference zone of the transonic wind tunnel support system has the advantages of simple and reliable structure, convenient and fast operation method, good repeatability, stronger adaptability and higher application value, and has important significance for improving the transonic wind tunnel test quality and optimizing the design of the model support mechanism.
Drawings
FIG. 1 is a schematic structural diagram of an axial static pressure probe tube used in the method for measuring the length of an interference zone of a transonic wind tunnel support system according to the present invention;
FIG. 2 is a schematic wind tunnel installation diagram of an axial static pressure probe tube used in the method for measuring the length of the disturbance zone of the transonic wind tunnel support system according to the present invention;
FIG. 3 is a supporting mechanism of embodiment 1;
FIG. 4 is a supporting mechanism of embodiment 2;
fig. 5 shows a support mechanism according to embodiment 3.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in FIG. 1, the measuring device used in the method for measuring the length of the disturbance zone of the transonic wind tunnel support system of the present invention is an axial static pressure probe tube; the head of the axial static pressure detection tube is a conical rotation body, a generatrix of the conical rotation body is an arc curve, the length of the conical rotation body is L, the diameter of the bottom of the conical rotation body is D, and the slenderness ratio of the head is L, D is (7-8): 1; the middle section of the axial static pressure detection tube is a cylindrical section, and the diameter of the cylindrical section is D; the back section of the axial static pressure detection tube is a cylindrical measurement section, the diameter of the cylindrical measurement section is D, and the cylindrical measurement section is provided with static pressure measurement points which are linearly arranged along the axis direction.
Example 1
The axial static pressure probe tube of the present embodiment has an overall length of 1.8m, L: D is 8:1, the mounting manner is shown in fig. 2, and the support mechanism is a straight head as shown in fig. 3.
The method for measuring the length of the interference zone of the transonic wind tunnel support system comprises the following steps:
a. installing an axial detection bent frame on a middle support of the transonic wind tunnel, starting the transonic wind tunnel under the condition that the Mach number Ma is 0.3, moving the axial detection bent frame according to a preset path, changing a measurement position until the measurement is finished, closing the transonic wind tunnel, and obtaining the Mach number distribution of a transonic wind tunnel core flow field with the Mach number of 0.3 after data processing to obtain a transonic wind tunnel flow correction result;
b. the method comprises the following steps of (1) removing an axial detection bent, installing a straight joint, and installing an axial static pressure detection pipe on the straight joint, wherein the axial static pressure detection pipe is positioned on a central axis of a transonic wind tunnel test section, and the head of the axial static pressure detection pipe faces to an incoming flow of a wind tunnel;
c. starting the transonic wind tunnel under the Mach number of 0.3, measuring the static pressure distribution of the central axis of the transonic wind tunnel test section by an axial static pressure detecting tube, and closing the transonic wind tunnel;
d. carrying out data processing to obtain Mach number distribution of the central axis of the transonic wind tunnel test section with Mach number of 0.3;
e. c, comparing the Mach number distribution of the central axis of the transonic wind tunnel test section obtained in the step d with the Mach number distribution of the transonic wind tunnel core flow field obtained in the step a, and finishing the measurement work of the axial static pressure probe tube if the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005; otherwise, moving the middle support towards the wind tunnel incoming flow direction through the transonic wind tunnel control system, and measuring the Mach number distribution of the central axis of the transonic wind tunnel test section again until the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005;
f. recording a first position where Mach number deviation of a corresponding measuring point is greater than or equal to 0.005, and calculating the distance from the first position to an outlet of a transonic wind tunnel test section to be 1.58m, wherein 1.58m is the length of an interference area with Mach number of 0.3;
g. repeating the steps a to f, and respectively obtaining the lengths of the interference areas of the transonic wind tunnel Mach numbers of 0.4, 0.5, 0.6, 0.7, 0.8, 0.9, 0.95 and 1.0, wherein specific data are shown in a table of test results of the lengths of the interference areas of different support systems in table 1.
Example 2
This example is substantially the same as the embodiment of example 1, and is mainly different in that the support mechanism is a joint of a double-shaft system as shown in fig. 4, and the lengths of the interference zones obtained are shown in table 1.
Example 3
This example is substantially the same as the embodiment of example 1, with the main difference being that the support mechanism is an optimized dual swivel joint as shown in fig. 5, and the length of the interference zone obtained is shown in table 1.
Table 1 length test result table for interference area of different support systems
| Ma | 0.3 | 0.4 | 0.5 | 0.6 | 0.7 | 0.8 | 0.9 | 0.95 | 1.0 |
| Flow field calibration | 1.20 | 1.45 | 1.60 | 1.60 | 1.60 | 1.60 | 1.60 | 1.60 | 1.30 |
| Straight joint | 1.58 | 1.64 | 1.73 | 1.76 | 1.76 | 1.79 | 1.94 | 1.94 | 1.79 |
| Double-rotating-shaft system joint | 1.73 | 1.85 | 1.94 | 2.00 | 2.21 | 2.21 | 2.21 | 2.15 | 1.94 |
| Optimized double-rotating-shaft system joint | 1.64 | 1.73 | 1.79 | 1.85 | 1.85 | 1.94 | 2.00 | 2.00 | 1.79 |
Although embodiments of the invention have been disclosed above, it is not intended to be limited to the uses set forth in the specification and examples, but rather, to one skilled in the art, all features of the invention disclosed, or all steps of any method or process so disclosed, may be combined in any suitable manner, except for mutually exclusive features and/or steps, without departing from the principles of the invention. It is therefore intended that the invention not be limited to the exact details and illustrations described and illustrated herein, but fall within the scope of the appended claims and equivalents thereof.
Claims (1)
1. A method for measuring the length of an interference zone of a transonic wind tunnel support system is characterized in that a measuring device used in the method is an axial static pressure detecting tube; the head of the axial static pressure detection tube is a conical rotation body, a generatrix of the conical rotation body is an arc curve, the length of the conical rotation body is L, the diameter of the bottom of the conical rotation body is D, and the slenderness ratio of the head is L, D is (7-8): 1; the middle section of the axial static pressure detection tube is a cylindrical section, and the diameter of the cylindrical section is D; the rear section of the axial static pressure detection tube is a cylindrical measurement section, the diameter of the cylindrical measurement section is D, and static pressure measurement points which are linearly arranged are arranged in the cylindrical measurement section along the axis direction; the method is characterized by comprising the following steps:
a. installing an axial detection bent frame on a middle support of the transonic wind tunnel, starting the transonic wind tunnel under the condition that the Mach number Ma is 0, moving the axial detection bent frame according to a preset path, changing a measurement position until the measurement is completed, closing the transonic wind tunnel, and obtaining the Mach number distribution of a transonic wind tunnel core flow field of the Mach number Ma0 after data processing to obtain a transonic wind tunnel flow correction result;
b. the method comprises the following steps of (1) removing an axial detection bent, installing a supporting mechanism, and installing an axial static pressure detection pipe on the supporting mechanism, wherein the axial static pressure detection pipe is positioned on a central axis of a transonic wind tunnel test section, and the head of the axial static pressure detection pipe faces to an incoming flow of a wind tunnel;
c. starting the transonic wind tunnel under the Mach number Ma0, measuring the static pressure distribution of the central axis of the transonic wind tunnel test section by an axial static pressure detecting tube, and closing the transonic wind tunnel;
d. carrying out data processing to obtain Mach number distribution of a central axis of the transonic wind tunnel test section with the Mach number Ma being Ma 0;
e. c, comparing the Mach number distribution of the central axis of the transonic wind tunnel test section obtained in the step d with the Mach number distribution of the transonic wind tunnel core flow field obtained in the step a, and finishing the measurement work of the axial static pressure probe tube if the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005; otherwise, moving the middle support towards the wind tunnel incoming flow direction through the transonic wind tunnel control system, and measuring the Mach number distribution of the central axis of the transonic wind tunnel test section again until the Mach number deviation of the corresponding measuring point is greater than or equal to 0.005;
f. recording a first position where Mach number deviation of a corresponding measuring point is greater than or equal to 0.005, and calculating the distance S from the first position to an outlet of a transonic wind tunnel test section, wherein S is the length of an interference area with Mach number Ma being Ma 0;
g. and (f) repeating the steps a to f to obtain the lengths of the interference areas under all Mach numbers of the transonic wind tunnel.
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Cited By (4)
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| CN113514219A (en) * | 2021-04-25 | 2021-10-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Periodic microstructure noise reduction device, noise suppression test system and method |
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| CN115048753A (en) * | 2022-08-16 | 2022-09-13 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel aerodynamic shape design method |
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| CN115048753A (en) * | 2022-08-16 | 2022-09-13 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel aerodynamic shape design method |
| CN115615655A (en) * | 2022-11-15 | 2023-01-17 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel test data interference correction method |
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Application publication date: 20210326 |