CN117129179B - Mach number correction method for double-support test under continuous wind tunnel wing - Google Patents
Mach number correction method for double-support test under continuous wind tunnel wing Download PDFInfo
- Publication number
- CN117129179B CN117129179B CN202311397382.1A CN202311397382A CN117129179B CN 117129179 B CN117129179 B CN 117129179B CN 202311397382 A CN202311397382 A CN 202311397382A CN 117129179 B CN117129179 B CN 117129179B
- Authority
- CN
- China
- Prior art keywords
- double
- support
- mach number
- under
- wing
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 65
- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000012937 correction Methods 0.000 title claims abstract description 27
- 239000000523 sample Substances 0.000 claims abstract description 35
- 238000003754 machining Methods 0.000 claims abstract description 4
- 230000003068 static effect Effects 0.000 claims description 31
- 238000004590 computer program Methods 0.000 claims description 13
- 238000012545 processing Methods 0.000 claims description 9
- 238000004364 calculation method Methods 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 description 6
- 230000006870 function Effects 0.000 description 3
- 238000010998 test method Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000002194 synthesizing effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
-
- 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
Abstract
The invention provides a Mach number correction method for a double-support test under a continuous wind tunnel wing, and belongs to the technical field of aerospace aerodynamic wind tunnel tests. The method comprises the following steps: s1, obtaining input conditions of a double-support-shaft probe tube under a wind tunnel wing; s2, designing a calibration device for machining double supports under the wing based on input conditions; s3, performing a wind tunnel under-wing double-support flow field calibration test based on the calibration device to obtain flow field parameters and Mach number control relations under different pressure conditions.
Description
Technical Field
The application relates to a Mach number correction method, in particular to a Mach number correction method for a double-support test under a continuous wind tunnel wing, and belongs to the technical field of aerospace aerodynamic wind tunnel tests.
Background
The conventional tail support force measuring mode has serious damage to the shape of the model rear body, has great influence on the pneumatic characteristics of the whole machine, and cannot meet the requirements of a high-precision force measuring test. In order to meet the requirements of bracket interference correction and airplane rear body aerodynamic characteristic research, a double-support double-balance force measurement test method is developed. The under-wing double-support system can not damage the tail of the model, and is very suitable for accurate measurement of the back body and a large aspect ratio model support interference test.
At present, the flow field calibration work of a large-scale continuous wind tunnel under-wing double-support system is not performed, and a complete under-wing double-support test flow field control relation is not established yet, so that 1) a certain deviation exists in the result of an under-wing double-support test; 2) The Mach number control relation of the incoming flow of the test section is inaccurate, so that Mach numbers cannot be aligned when the correction data are interfered under the single-double support condition, and the correction quantity is deviated; 3) In the double support test, the core flow control relation is changed due to the existence or non-existence of false tail support, so that the resistance correction amount is abnormal under the transonic condition (resistance divergence M).
Disclosure of Invention
The following presents a simplified summary of the invention in order to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention. Its purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.
In view of this, in order to solve at least one of the above-mentioned technical problems, the present invention provides a mach number correction method for a double-support test under a continuous wind tunnel wing, which is suitable for a double-support test of a 2.4 meter wind tunnel.
The Mach number correction method for the double-support test under the continuous wind tunnel wing comprises the following steps:
s1, obtaining input conditions of a double-support-shaft probe tube under a wind tunnel wing;
s2, designing a calibration device for machining double supports under the wing based on input conditions;
s3, performing a double-support flow field calibration test under the wind tunnel wing based on the calibration equipment to obtain the flow field parameter and Mach number relation under different tunnel body conditions, wherein the method comprises the following steps:
s31, installing the calibrating and testing equipment in the double-support mechanism under the wind tunnel wing, performing a flow field calibrating and testing test, and processing data obtained by each static pressure measuring point of the double-support shaft probe tube to obtain average Mach number, mach number distribution root mean square deviation and Mach number deviation parameters of a model area;
s32, according to the parameters obtained in the step S31, establishing a corresponding relation between the resident chamber Mach number and the core leveling average Mach number of the under-wing dual-support model area under different pressures, and finally realizing the flow field control target by controlling the resident chamber Mach number.
Preferably, the method for obtaining the input condition of the double-support-shaft probe tube under the wind tunnel wing comprises the following steps:
s11, establishing a digital model of the double-support-shaft probe tube in the wind tunnel test section by using CFD software, dividing grids, and calculating pressure distribution of the double-support-shaft probe tube under different tunnel conditions;
s12, setting different lengths and different diameters of the double-support-shaft probe tube, and respectively calculating pressure distribution of the double-support-shaft probe tube in various states;
s13, setting plugging cones with different plugging degrees at the rear ends of the double-support-shaft exploratory tubes, and calculating pressure distribution of the double-support-shaft exploratory tubes under different conditions.
Preferably, according to the data result obtained by flow field calibration, a corresponding relation between the resident chamber Mach number and the core leveling average Mach number of the under-wing dual-support model area under different pressures is established, and the method for realizing the flow field control target by controlling the resident chamber Mach number is as follows:
measuring central axis static pressure of a double-support model area under the wing by using a double-support shaft probe tube, measuring the static pressure of a resident chamber by using a resident chamber static pressure sensor, and measuring the total pressure of a wind tunnel by using a total pressure sensor;
calculating based on the static pressure of the measuring point of the double-support-shaft detecting pipe, the static pressure of the resident chamber and the total pressure of the wind tunnel to obtain a flow field calibration result, and obtaining the corresponding relation between the core leveling average Mach number and the resident chamber Mach number of the under-wing double-support model area;
the fake tail support rod outer cover is additionally arranged on the double-support shaft probe tube, and the steps are repeated, so that the corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area under the condition of the fake tail support rod is obtained;
controlling cavity conditions by using the obtained corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area, and realizing a flow field control target;
if the flow field index of the under-wing dual-support core flow obtained through the test meets the design requirement, determining the under-cavity condition of each resident chamber; if the flow field index of the under-wing dual-support core flow obtained through the test does not meet the design requirement, the flow field is controlled again through the obtained control relation, and finally the control relation meeting the design index requirement is obtained.
Preferably, the method for processing the data measured by the double-support-shaft probe tube comprises the following steps: the sub-transonic speed utilizes the total pressure of the stabilizing tube and the static pressure of each measuring point, and the calculation formula of the measuring point doherty is as follows:
；
wherein,representing Mach number, P, at the ith point in the model region 0 Representing the total pressure of the test section, P i The static pressure value measured by the static pressure measuring point of the double-support-shaft probe tube is represented;
model zone average Mach numberRoot mean square deviation of Mach number distribution->Mach number deviation->And maximum Mach number deviation +.>The calculation formula of (2) is as follows:
；
；
wherein,representing the total number of each measuring point in the model area;
the mach number axial gradient is calculated as follows:
；
when the Mach number of a row of measuring points on the central line or the side wall of the transonic test section is measured,representing the distance between the ith point and the inlet of the test section; />And the total number of the measuring points in the model area is represented.
The second scheme is an electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor implements the Mach number correction method of the continuous wind tunnel wing under-wing double-support test in the first scheme when executing the computer program.
A third aspect is a computer readable storage medium, on which a computer program is stored, where the computer program when executed by a processor implements a mach number correction method for a continuous wind tunnel under-wing double-support test as described in the first aspect.
The beneficial effects of the invention are as follows: the invention establishes a complete set of continuous type wind tunnel under-wing double-support Mach number control relation, obtains complete flow field parameters, perfects an under-wing double-support test method, and solves the problems that 1) a certain deviation exists in the result of the under-wing double-support test; 2) The Mach number control relation of the incoming flow of the test section is inaccurate, so that Mach numbers cannot be aligned when the correction data are interfered under the single-double support condition, and the correction quantity is deviated; 3) In the double-support test, the core flow control relation can be changed due to the existence or non-false tail support, so that the resistance correction amount is abnormal under the transonic condition (resistance divergence M).
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute an undue limitation to the application. In the drawings:
FIG. 1 is a flow chart of a Mach number correction method for a double support test under a continuous wind tunnel wing.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following detailed description of exemplary embodiments of the present application is given with reference to the accompanying drawings, and it is apparent that the described embodiments are only some of the embodiments of the present application and not exhaustive of all the embodiments. It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other.
Example 1: referring to fig. 1, a mach number correction method for a double-support test under a continuous wind tunnel wing according to the present embodiment includes the steps of:
s1, obtaining input conditions of a double-support-shaft probe tube under a wind tunnel wing;
s11, establishing a digital model of the double-support-shaft probe tube under the inner wing of the wind tunnel test section by using CFD software, dividing grids, and calculating pressure distribution of the double-support-shaft probe tube under different hole conditions;
s12, setting different lengths and different diameters of the double-support-shaft probe tube, and respectively calculating pressure distribution of the double-support-shaft probe tube in various states;
s13, setting plugging cones with different plugging degrees at the rear end of the double-support-shaft probe tube, and calculating pressure distribution of the double-support-shaft probe tube under different conditions;
s2, designing a calibration device for machining double supports under the wing based on input conditions;
s3, performing a double-support flow field calibration test under the wind tunnel wing based on the calibration equipment to obtain flow field parameters and Mach number control relations under different tunnel body conditions;
s31, installing the calibrating and testing equipment in the double-support mechanism under the wind tunnel wing, performing a flow field calibrating and testing test, and processing data obtained by each static pressure measuring point of the double-support shaft probe tube to obtain average Mach number, mach number distribution root mean square deviation and Mach number deviation parameters of a model area;
the method for processing the data obtained by each static pressure measuring point of the double-support-shaft probe tube comprises the following steps: the sub-transonic speed utilizes the total pressure of the stabilizing tube and the static pressure of each measuring point, and the calculation formula of the measuring point doherty is as follows:
；
wherein,representing Mach number, P, at the ith point in the model region 0 Representing the total pressure of the test section, P i The static pressure value measured by the static pressure measuring point of the double-support-shaft probe tube is represented;
whether the pressure transonic or supersonic velocity, the total pressure of the stable section can be used for replacing the total pressure P of the test section 0 。
Model zone average Mach numberRoot mean square deviation of Mach number distribution->Mach number deviation->And maximum Mach number deviation +.>The calculation formula of (2) is as follows:
；
；
wherein,representing the total number of each measuring point in the model area;
the mach number axial gradient is calculated as follows:
；
when the Mach number of a row of measuring points on the central line or the side wall of the transonic test section is measured,representing the distance between the ith point and the inlet of the test section; />Representing the total number of measuring points in the model area;
s32, according to the parameters obtained in the step S31, establishing a corresponding relation between the resident chamber Mach number and the core leveling average Mach number of the under-wing dual-support model area under different pressures, and finally realizing the flow field control target by controlling the resident chamber Mach number.
According to the corresponding relation between the core flow and the residence, the corresponding relation between the static blade angle, the rotating speed, the residence Mach number of the compressor under different pressures and the core leveling average Mach number and the total wind tunnel temperature control range of the under-wing dual-support model area is established, and the residence is controlled to realize the flow field control target:
measuring central axis static pressure of a double-support model area under the wing by using a double-support shaft probe tube, measuring the static pressure of a resident chamber by using a resident chamber static pressure sensor, and measuring the total pressure of a wind tunnel by using a total pressure sensor;
calculating based on the static pressure of the measuring point of the double-support-shaft detecting pipe, the static pressure of the resident chamber and the total pressure of the wind tunnel to obtain a flow field calibration result, and obtaining the corresponding relation between the core leveling average Mach number and the resident chamber Mach number of the under-wing double-support model area;
the fake tail support rod outer cover is additionally arranged on the double-support shaft probe tube, and the steps are repeated, so that the corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area under the condition of the fake tail support rod is obtained;
controlling cavity conditions by using the obtained corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area, and realizing a flow field control target;
the wind tunnel body conditions comprise a wallboard angle, a Flap opening, a compressor rotating speed and the like, so that Mach number control relation and core flow field indexes under the conditions of all the tunnel bodies are obtained.
Through the test items, the corresponding relation among the static blade angle, the rotating speed, the resident chamber Mach number, the core leveling average Mach number of the under-wing dual-support model area and the total temperature control range of the wind tunnel of the compressor under different pressures is established.
The method comprises the steps of obtaining the accuracy of the relation between the double-support core flow under the control wing and a residence chamber and the core flow field index under each cavity condition by controlling the corresponding wind tunnel body condition under each Mach number of the double-support core flow under the wing;
if the flow field index of the under-wing dual-support core flow obtained through the test meets the design requirement, determining the under-cavity condition of each resident chamber; if the flow field index of the under-wing dual-support core flow obtained through the test does not meet the design requirement, performing flow field control again through the obtained control relation, and finally obtaining the control relation meeting the design index requirement;
s4, carrying out an under-wing double-support standard mode force test according to a flow field parameter and Mach number control relation to obtain an under-wing double-support interference quantity, and verifying the accuracy of the Mach number correction quantity, wherein the method comprises the following steps of:
the under-wing double-support standard die force test comprises a false tail support rod test and a no-false tail support rod test, and the experimental process is as follows:
synthesizing the double balance load under the same coordinate system to obtain the load of the model, and measuring the installation angle of the balance and the attitude angle of the balance relative to the horizontal plane;
decomposing the load of the balance into a ground shaft system, superposing the load in the ground shaft system, and subtracting the dead weight load from the total load of the model under the ground shaft system to obtain the pneumatic load of the model;
using the model angle measured under the ground shaft system to project aerodynamic force under the ground shaft system to the model body shaft system and the wind shaft system;
after the experiment is finished, interpolating aerodynamic force under a body shafting or a wind shafting according to the attack angle of the model;
the difference value between aerodynamic data of the support rod with the false tail and aerodynamic data of the support rod without the false tail under the same attack angle and the same shafting is a supporting interference quantity;
and comparing the supporting interference quantity with data obtained by a test method adopted in the prior art, wherein the deviation is within 10%, which indicates that the Mach number correction accuracy meets the requirement.
Example 2: the computer device of the present invention may be a device including a processor and a memory, such as a single chip microcomputer including a central processing unit. And the processor is used for executing the computer program stored in the memory to realize the Mach number correction method of the continuous wind tunnel under-wing double-support test.
The processor may be a central processing unit (Central Processing Unit, CPU), other general purpose processors, digital signal processors (Digital Signal Processor, DSP), application specific integrated circuits (Application Specific Integrated Circuit, ASIC), off-the-shelf programmable gate arrays (Field-Programmable Gate Array, FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or the like. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The memory may mainly include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program (such as a sound playing function, an image playing function, etc.) required for at least one function, and the like; the storage data area may store data (such as audio data, phonebook, etc.) created according to the use of the handset, etc. In addition, the memory may include high-speed random access memory, and may also include non-volatile memory, such as a hard disk, memory, plug-in hard disk, smart Media Card (SMC), secure Digital (SD) Card, flash Card (Flash Card), at least one disk storage device, flash memory device, or other volatile solid-state storage device.
Example 3: computer-readable storage medium embodiments
The computer readable storage medium of the present invention may be any form of storage medium that is readable by a processor of a computer device, including but not limited to, nonvolatile memory, volatile memory, ferroelectric memory, etc., on which a computer program is stored, and when the processor of the computer device reads and executes the computer program stored in the memory, the steps of a mach number correction method of the continuous wind tunnel under-wing double-support test described above may be implemented.
The computer program comprises computer program code which may be in source code form, object code form, executable file or in some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth. It should be noted that the computer readable medium contains content that can be appropriately scaled according to the requirements of jurisdictions in which such content is subject to legislation and patent practice, such as in certain jurisdictions in which such content is subject to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.
While the invention has been described with respect to a limited number of embodiments, those skilled in the art, having benefit of the above description, will appreciate that other embodiments are contemplated within the scope of the invention as described herein. Furthermore, it should be noted that the language used in the specification has been principally selected for readability and instructional purposes, and may not have been selected to delineate or circumscribe the inventive subject matter. Accordingly, many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the appended claims. The disclosure of the present invention is intended to be illustrative, but not limiting, of the scope of the invention, which is defined by the appended claims.
Claims (6)
1. The Mach number correction method for the double-support test under the continuous wind tunnel wing is characterized by comprising the following steps of:
s1, obtaining input conditions of a double-support-shaft probe tube under a wind tunnel wing;
s2, designing a calibration device for machining double supports under the wing based on input conditions;
s3, performing a double-support flow field calibration test under the wind tunnel wing based on the calibration device to obtain the relation between flow field parameters and Mach numbers under different pressure conditions, wherein the method comprises the following steps:
s31, installing the calibrating and testing equipment in the double-support mechanism under the wind tunnel wing, performing a flow field calibrating and testing test, and processing data obtained by each static pressure measuring point of the double-support shaft probe tube to obtain average Mach number, mach number distribution root mean square deviation and Mach number deviation parameters of a model area;
s32, according to the parameters obtained in the step S31, establishing a corresponding relation between the resident chamber Mach number and the core leveling average Mach number of the under-wing dual-support model area under different pressures, and finally realizing the flow field control target by controlling the resident chamber Mach number.
2. The Mach number correction method for a double support test under a continuous wind tunnel wing according to claim 1, wherein the method for obtaining the input condition of the double support shaft probe is as follows:
s11, establishing a digital model of the double-support-shaft probe tube in the wind tunnel test section by using CFD software, dividing grids, and calculating pressure distribution of the double-support-shaft probe tube under different tunnel conditions;
s12, setting different lengths and different diameters of the double-support-shaft probe tube, and respectively calculating pressure distribution of the double-support-shaft probe tube in various states;
s13, setting plugging cones with different plugging degrees at the rear ends of the double-support-shaft exploratory tubes, and calculating pressure distribution of the double-support-shaft exploratory tubes under different conditions.
3. The method for correcting mach number of continuous wind tunnel under-wing double-support test according to claim 2, wherein the method for realizing flow field control target by controlling the resident mach number is characterized in that the corresponding relation between the resident mach number and the core leveling average mach number of the under-wing double-support model area under different pressures is established according to the data result obtained by flow field calibration, and comprises the following steps:
measuring central axis static pressure of a double-support model area under the wing by using a double-support shaft probe tube, measuring the static pressure of a resident chamber by using a resident chamber static pressure sensor, and measuring the total pressure of a wind tunnel by using a total pressure sensor;
calculating based on the static pressure of the measuring point of the double-support-shaft detecting pipe, the static pressure of the resident chamber and the total pressure of the wind tunnel to obtain a flow field calibration result, and obtaining the corresponding relation between the core leveling average Mach number and the resident chamber Mach number of the under-wing double-support model area;
the fake tail support rod outer cover is additionally arranged on the double-support shaft probe tube, and the steps are repeated, so that the corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area under the condition of the fake tail support rod is obtained;
and controlling the cavity conditions by using the obtained corresponding relation between the core leveling average Mach number and the resident Mach number of the under-wing double-support model area, so as to realize the flow field control target.
4. A mach number correction method for a double-support test under a continuous wind tunnel wing according to claim 3, wherein the method for processing the data obtained by each static pressure measuring point of the double-support shaft probe is as follows: the sub-transonic speed utilizes the total pressure of the stabilizing tube and the static pressure of each measuring point, and the calculation formula of the measuring point doherty is as follows:
;
wherein,representing Mach number, P, at the ith point in the model region 0 Representing the total pressure of the test section, P i The static pressure value measured by the static pressure measuring point of the double-support-shaft probe tube is represented;
model zone average Mach numberRoot mean square deviation of Mach number distribution->Mach number deviation->And maximum Mach number deviation +.>The calculation formula of (2) is as follows:
;
wherein,representing the total number of each measuring point in the model area;
the mach number axial gradient is calculated as follows:
;
when the Mach number of a row of measuring points on the central line or the side wall of the transonic test section is measured,representing the distance between the ith point and the inlet of the test section; />And the total number of the measuring points in the model area is represented.
5. An electronic device comprising a memory and a processor, the memory storing a computer program, the processor implementing the steps of a mach number correction method for a continuous wind tunnel under-wing double-support test as claimed in any one of claims 1 to 4 when executing the computer program.
6. A computer readable storage medium having stored thereon a computer program, which when executed by a processor implements a mach number correction method of a continuous wind tunnel under-wing double support test according to any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311397382.1A CN117129179B (en) | 2023-10-26 | 2023-10-26 | Mach number correction method for double-support test under continuous wind tunnel wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311397382.1A CN117129179B (en) | 2023-10-26 | 2023-10-26 | Mach number correction method for double-support test under continuous wind tunnel wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117129179A CN117129179A (en) | 2023-11-28 |
| CN117129179B true CN117129179B (en) | 2023-12-26 |
Family
ID=88851147
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311397382.1A Active CN117129179B (en) | 2023-10-26 | 2023-10-26 | Mach number correction method for double-support test under continuous wind tunnel wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117129179B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010243400A (en) * | 2009-04-08 | 2010-10-28 | Japan Aerospace Exploration Agency | Building berth support interference correcting method in subsonic half model wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
| CN111999029A (en) * | 2020-10-26 | 2020-11-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Supporting device for propeller test |
| CN212779853U (en) * | 2020-09-23 | 2021-03-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section |
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN115219141A (en) * | 2022-08-01 | 2022-10-21 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel force measurement test method of double support rods and double balances |
| 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 |
| CN116929703A (en) * | 2023-09-18 | 2023-10-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Low-temperature wind tunnel Mach number determination method considering blocking effect and application thereof |
-
2023
- 2023-10-26 CN CN202311397382.1A patent/CN117129179B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010243400A (en) * | 2009-04-08 | 2010-10-28 | Japan Aerospace Exploration Agency | Building berth support interference correcting method in subsonic half model wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
| CN212779853U (en) * | 2020-09-23 | 2021-03-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section |
| CN111999029A (en) * | 2020-10-26 | 2020-11-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Supporting device for propeller test |
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN115219141A (en) * | 2022-08-01 | 2022-10-21 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel force measurement test method of double support rods and double balances |
| 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 |
| CN116929703A (en) * | 2023-09-18 | 2023-10-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Low-temperature wind tunnel Mach number determination method considering blocking effect and application thereof |
Non-Patent Citations (3)
| Title |
|---|
| 2.4m跨声速风洞槽壁试验段调试及流场校测;陈德华;王瑞波;刘光远;师建元;尹陆平;;实验流体力学(04);第66-70页 * |
| 大型客机低速构型高雷诺数风洞腹撑支架干扰数值模拟;王继明;高云海;焦仁山;;航空学报(04);第1-11页 * |
| 跨声速风洞中轴探管的应用;吴盛豪;裴海涛;陈吉明;陈钦;;航空动力学报(10);第156-162页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117129179A (en) | 2023-11-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106096223B (en) | Five-hole probe data processing method | |
| CN108982915A (en) | A kind of acceleration transducer temperature-compensation method | |
| CN113947035A (en) | Data heaven-earth correlation method for transition of hypersonic velocity boundary layer | |
| CN115358026A (en) | Five-hole probe data processing method based on multivariate linear regression and surface fitting | |
| CN109583067B (en) | Design method of high-speed aircraft transition position measurement sensor based on temperature balance | |
| CN111950148A (en) | Method and device for calculating inner wall temperature of test run of liquid rocket thrust chamber | |
| Jiao et al. | A two-dimensional temperature correction method for pressure-sensitive paint measurement on helicopter rotor blades | |
| CN117129179B (en) | Mach number correction method for double-support test under continuous wind tunnel wing | |
| CN111189403B (en) | Tunnel deformation monitoring method and device and computer readable storage medium | |
| CN116659803A (en) | Method for acquiring aerodynamic load of continuous wind tunnel based on balance zero point on-line monitoring | |
| CN113405805B (en) | Aero-engine inlet flow obtaining method considering boundary layer of air inlet channel | |
| CN107991637A (en) | impedance measuring instrument calibration method and device | |
| CN110646134B (en) | Calibration method and calibration device for air pressure sensor | |
| CN111487440A (en) | Calibration method of five-hole probe | |
| CN116168090B (en) | Equipment parameter calibration method and device | |
| CN116380396A (en) | Continuous wind tunnel aircraft atmospheric data system identification test system and method | |
| CN109344522B (en) | Method and system for calculating grinding quantity of stationary blade of axial flow compressor | |
| CN112033331A (en) | Group hole measurement swing angle planning method based on three-coordinate measuring needle | |
| CN107239602A (en) | A kind of probe antenna model quick calculation method based on curve matching | |
| EP2866205A2 (en) | Three-dimensional model generation apparatus, three-dimensional model generation method, and program | |
| CN115642913A (en) | Analog-to-digital converter ADC calibration method, device, equipment and storage medium | |
| CN110580391B (en) | Fundamental frequency mode measurement method of flexible structure | |
| CN109446703B (en) | Stay cable aerodynamic resistance determination method and device and terminal equipment | |
| CN108106634A (en) | Star sensor internal parameter calibration method for direct star observation | |
| CN105547633A (en) | Subsonic speed wind tunnel force test zero resistance correction 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 |