CN114593889A - Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area - Google Patents
Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area Download PDFInfo
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Abstract
The invention belongs to the technical field of high-speed free jet wind tunnel tests and discloses a method for obtaining static pressure matching precision of a large-range supersonic jet uniform area. The method for rapidly acquiring the static pressure matching precision of the uniform area of the large-range supersonic jet flow comprises the following steps of: arranging static pressure measuring points in the high-speed free jet flow wind tunnel; determining the total pressure of the wind tunnel stable section; starting the high-speed free jet wind tunnel in a constant total pressure operation mode; collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably; closing the high-speed free jet wind tunnel; and (6) processing data to obtain the static pressure matching precision. The method for rapidly acquiring the static pressure matching precision of the uniform area of the supersonic jet in a large range is simple and clear in thought, full in theoretical basis, capable of meeting the Mach number change requirement and the wind tunnel pressure control performance requirement, beneficial to accurately acquiring the static pressure matching precision of the supersonic jet of the high-speed free jet wind tunnel, and high in engineering application value.
Description
Technical Field
The invention belongs to the technical field of high-speed free jet wind tunnel tests, and particularly relates to a method for obtaining static pressure matching precision of a large-range supersonic jet uniform area.
Background
When a traditional high-speed free jet wind tunnel is used for supersonic speed tests, the mode of improving the running total pressure is usually adopted for blowing, and the mode can ensure that a rhombic area at the outlet of a spray pipe is uniform airflow. And the gas flow outside the diamond area and inside the jet boundary can carry out repeated expansion acceleration and compression deceleration processes, so that the quality of the flow field outside the diamond area is rapidly deteriorated. The uniform airflow in the rhombic area can be subjected to tests with small requirements on the uniform area range, such as a small attack angle air inlet channel, engine characteristics and the like, and the model scale cannot exceed the rhombic area range. Other blowing tests with low requirements on the quality of the convection field can also be carried out in a larger jet flow range. But the uniform flow field range of the diamond area is too small, so that the high-quality test requirements of a large-attack-angle air inlet channel, air inlet/engine body/engine integration, thrust vector characteristics, a large-scale model and the like are difficult to meet.
The high-speed free jet wind tunnel has the obvious advantages that the blockage degree of a model is allowed to be large, but the uniform area of the supersonic jet flow field in the traditional operation mode is small, and the function exertion of the high-speed free jet wind tunnel is limited. The adoption of the static pressure matching point mode can only adapt to the condition that the model state is unchanged or has small change, and once the model state has large change, the matching pressure of the flow field needs to be correspondingly changed at the same time to keep the supersonic flow field to have a larger uniform area range.
In order to meet the urgent need of advanced aircraft development for the flow field simulation capability of a large-range supersonic jet flow uniform area, a method for rapidly obtaining the static pressure matching precision of the large-range supersonic jet flow uniform area is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for rapidly obtaining the static pressure matching precision of a large-range supersonic jet flow uniform area.
The invention discloses a method for obtaining static pressure matching precision of a large-range supersonic jet flow uniform area, which is characterized in that the method is used for a high-speed free jet flow wind tunnel, the high-speed free jet flow wind tunnel sequentially comprises a spray pipe, a test cabin and a collector from front to back according to the airflow direction of the wind tunnel, and the method comprises the following steps:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point at the nozzle outlet of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point on the inner wall of the test chamber;
Selecting supersonic velocity spray pipes according to the high-speed free jet wind tunnel, and determining the total pressure of the stable section of the wind tunnel according to the Mach number of the supersonic velocity spray pipes;
S03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnel;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
and (3) judging whether the high-speed free jet wind tunnel enters stable operation through the total pressure judging condition, continuously and stably operating for T seconds, and continuously acquiring the static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin in the operating time interval (T1, T2)Static pressure at the nozzle outletTotal pressure of stable section of wind tunnelObtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabinNozzle outlet static pressure arrayTotal pressure array for wind tunnel stabilizing section,;
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, data processing is carried out, and static pressure matching precision is obtained;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (T1, T2)And minimum value;
calculating the static pressure matching precision of the Mach number of the supersonic velocity spray pipe:。
the method for rapidly acquiring the static pressure matching precision of the uniform area of the large-range supersonic jet flow is characterized by firstly starting total pressure based on Mach number matching operation corresponding to a supersonic jet pipe, blowing in a constant total pressure starting mode, measuring and acquiring a reference point static pressure of a test cabin, a static pressure of an outlet of the jet pipe and a total pressure of a stable section in real time through a pressure acquisition system of a high-speed free jet flow wind tunnel, performing total pressure control according to preset wind tunnel total pressure control precision, and turning off the vehicle after stably operating for a period of time; correspondingly extracting a test chamber static pressure array measured by a test chamber static pressure measuring point according to the collected total pressure stable operation pressure time interval, and subtracting the minimum value from the maximum value of the test chamber static pressure array to obtain a maximum fluctuation value of the test chamber static pressure; correspondingly extracting a static pressure array of the outlet of the spray pipe measured by the static pressure measuring point of the outlet of the spray pipe in the time interval, and averaging the static pressure array of the outlet of the spray pipe to obtain the average static pressure of the outlet of the spray pipe; and comparing the maximum fluctuation value of the static pressure of the test chamber with the reference static pressure at the outlet of the spray pipe to obtain the static pressure matching precision of the reference point static pressure of the test chamber and the static pressure at the outlet of the spray pipe.
The method for rapidly obtaining the static pressure matching precision of the uniform area of the large-range supersonic jet can provide guidance for the matching precision of the static pressures of the outlets of the spray pipes with different supersonic mach numbers of the high-speed free jet wind tunnel and the static pressure of the reference point of the test cabin, and is an effective method for pertinently improving the static pressure matching precision of different supersonic mach numbers; the problem that the uniformity of a flow field is poor or exceeds the pressure regulation capability of the wind tunnel due to the fact that the same static pressure matching precision is adopted due to the fact that the Mach numbers of different supersonic speeds are different is solved; the method can provide the best individualized static pressure matching precision for different supersonic mach number flow fields of the high-speed free jet wind tunnel, and further improve the flow field uniformity of the high-speed free jet wind tunnel.
The method for rapidly acquiring the static pressure matching precision of the uniform area of the supersonic jet in a large range is simple and clear in thought, full in theoretical basis, capable of meeting the Mach number change requirement and the wind tunnel pressure control performance requirement, beneficial to accurately acquiring the static pressure matching precision of the supersonic jet of the high-speed free jet wind tunnel, and high in engineering application value.
Drawings
FIG. 1 is a static pressure measuring point layout diagram in the method for obtaining the static pressure matching precision of the large-range supersonic jet flow uniform area of the invention;
FIG. 2 is a flow chart of a method of the present invention for obtaining static pressure matching accuracy for a uniform region of a wide range of supersonic jet flows;
FIG. 3 is a graph of the total pressure in the time-stabilization phase obtained in example 1.
In the figure, 1, a static pressure measuring point at the outlet of a spray pipe; 2. a test chamber reference point static pressure test point; 3. a nozzle outlet; 4. a test chamber; 5. a collector.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in figure 1, the high-speed free jet wind tunnel sequentially comprises a spray pipe, a test chamber 4 and a collector 5 from front to back according to the wind tunnel airflow direction. The supersonic nozzle mach number is 1.5.
As shown in fig. 2, the implementation steps of this embodiment are as follows:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point 1 at a nozzle outlet 3 of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point 2 on the inner wall of a test chamber 4;
Selecting supersonic velocity spray pipes according to the high-speed free jet wind tunnel, and determining the total pressure of the stable section of the wind tunnel according to the Mach number of the supersonic velocity spray pipesIs 192 KPa;
s03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling the total pressure and the total pressure according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnelControlling;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
after the high-speed free jet wind tunnel is judged to enter the stable operation for about 8 seconds through the total pressure judging condition that the total pressure enters a control interval of 0.5 percent, the high-speed free jet wind tunnel continuously operates stably, and the static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin is continuously collected in the operation time interval (25, 32.1) shown in figure 3Static pressure at the nozzle outletTotal pressure of stable section of wind tunnelObtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabinNozzle outlet static pressure arrayTotal pressure array for wind tunnel stabilizing section,,;
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, data processing is carried out, and static pressure matching precision is obtained;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (25, 32.1)And minimum value;
calculating the static pressure matching precision of the Mach number of the supersonic velocity spray pipe:。
although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements will readily occur to those skilled in the art without departing from the principles of the present invention, and the present invention is not limited to the specific details and illustrations shown and described herein.
Claims (1)
1. The method for obtaining the static pressure matching precision of the uniform area of the supersonic jet flow in a large range is characterized in that the method is used for a high-speed free jet flow wind tunnel, and the high-speed free jet flow wind tunnel sequentially comprises a spray pipe, a test cabin (4) and a collector (5) from front to back according to the airflow direction of the wind tunnel, and the method comprises the following steps of:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point (1) at a nozzle outlet (3) of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point (2) on the inner wall of a test chamber (4);
Selecting supersonic velocity spray pipes according to the high-speed free jet wind tunnel, and determining the total pressure of the stable section of the wind tunnel according to the Mach number of the supersonic velocity spray pipes;
S03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnel;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
and (3) judging whether the high-speed free jet wind tunnel enters stable operation through the total pressure judging condition, continuously and stably operating for T seconds, and continuously acquiring the static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin in the operating time interval (T1, T2)Static pressure at the nozzle outletTotal pressure of stable section of wind tunnelObtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabinNozzle outlet static pressure arrayTotal pressure array for wind tunnel stabilizing section,;
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, data processing is carried out, and static pressure matching precision is obtained;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (T1, T2)And minimum value;
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Cited By (2)
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CN116296226A (en) * | 2023-05-23 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | Flow field control method for 1 meter-level direct current temporary flushing blowing guiding type hypersonic wind tunnel |
CN117647374A (en) * | 2024-01-25 | 2024-03-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining migration speed of high-speed jet shear layer based on dynamic pressure data |
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Cited By (3)
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CN116296226A (en) * | 2023-05-23 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | Flow field control method for 1 meter-level direct current temporary flushing blowing guiding type hypersonic wind tunnel |
CN117647374A (en) * | 2024-01-25 | 2024-03-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining migration speed of high-speed jet shear layer based on dynamic pressure data |
CN117647374B (en) * | 2024-01-25 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining migration speed of high-speed jet shear layer based on dynamic pressure data |
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