CN114608792B - Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe - Google Patents
Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe Download PDFInfo
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Abstract
The invention belongs to the technical field of high-speed wind tunnel tests and discloses a method for measuring a sub-transonic jet flow field uniform region of a high-speed jet wind tunnel by using a short shaft probe. The method comprises the following steps: installing a short axial detection tube; starting a high-speed jet wind tunnel; collecting static pressure data of a sub-transonic speed jet flow field; calculating the Mach number of each measurement point; calculating the Mach number difference of each measurement point; determining a jet boundary point; determining a test section uniform area of the high-speed jet wind tunnel; and calculating the root mean square deviation value of the test section uniform area of the high-speed jet wind tunnel. The method is suitable for measuring the boundary and the uniformity of the uniform area of the sub-transonic jet flow field of the high-speed jet wind tunnel, the boundary of the uniform area of the sub-transonic jet flow is measured by using the overall movement of the short axial detection tube, the disturbance influence on the sub-transonic jet flow field is reduced to the maximum extent, the method is simple and clear, the theoretical basis is sufficient, the boundary of the uniform area of the sub-transonic jet flow can be rapidly and accurately obtained, and the usable flow field range of the sub-transonic test of the high-speed jet wind tunnel is measured.
Description
Technical Field
The invention belongs to the technical field of high-speed wind tunnel tests, and particularly relates to a method for measuring a sub-transonic jet flow field uniform region of a high-speed jet wind tunnel by using a short shaft probe.
Background
The high-speed jet wind tunnel is a high-speed wind tunnel with a special structure form, high-speed airflow ejected from a nozzle of the high-speed jet wind tunnel directly enters static gas of a test chamber, high-speed jet flow and the static gas interact to form an unstable gas turbulence mixing layer, namely a high-speed jet flow boundary, an area within the boundary is called a jet flow constant-speed area and becomes a jet flow uniform area, and a test model is generally required to be located within the jet flow uniform area in a high-speed jet flow wind tunnel test.
When the conventional high-speed closed wind tunnel is in a sub-transonic speed, disturbance can be transmitted in a full flow field, and the Mach number distribution uniformity on the central line of the test section can represent the Mach number distribution uniformity of the whole test section, so that the sub-transonic speed field of the conventional high-speed closed wind tunnel is used for calibrating and mainly measuring the distribution uniformity of the Mach number in the center (core flow) of the test section. Generally, when an axial detecting tube is used for measuring a core flow field in a conventional high-speed closed wind tunnel, the axial detecting tube is long, the head of the long axial detecting tube is required to be tensioned by a steel rope after the long axial detecting tube is installed on a rigid support so as to ensure that the head of the long axial detecting tube does not shake to interfere with the flow field, the long axial detecting tube is fixedly installed in the wind tunnel and cannot move freely, and the method is difficult to measure the uniform area range and the uniformity index of the flow field in an opening test section of the high-speed jet wind tunnel.
For a high-speed jet wind tunnel, a test section is not shielded by a wall plate, the blockage degree of a model is allowed to be larger, however, after the core flow of the sub-transonic jet flow field is emitted from the outlet of the spray pipe, momentum exchange is carried out between the core flow and surrounding particles to form a turbulent boundary layer, the thickness of the boundary layer is continuously increased along with the direction far away from the initial section of the outlet, the range of the core flow is continuously contracted, and the uniformity of the core flow field needs to be measured, and the boundary of a uniform area needs to be determined so as to determine the range of the flow field available for the model test.
At present, a method for measuring a sub-transonic jet flow field uniform region of a high-speed jet wind tunnel by using a short shaft probe is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for measuring a sub-transonic jet flow field uniform region of a high-speed jet wind tunnel by using a short shaft probe.
The invention discloses a method for measuring a sub-transonic jet flow field uniform region of a high-speed jet wind tunnel by using a short shaft probe, which comprises the following steps of:
s01, mounting a short axial detection tube;
installing a short axial detection tube on a four-degree-of-freedom motion mechanism of the high-speed jet wind tunnel, wherein the central axis of the short axial detection tube is parallel to the central axis of the high-speed jet wind tunnel; the origin of coordinates O is located at the point where the central axis of the high-speed jet wind tunnel intersects with the section of the outlet of the nozzle of the high-speed jet wind tunnel, the OX axis is located on the central axis, the forward direction along the airflow direction is the positive X direction, the Y axis is vertically upward, and the Z axis accords with the right-hand rule; the four-freedom-degree motion mechanism has X-direction freedom degrees and Y-direction freedom degrees;
s02, starting a high-speed jet wind tunnel;
starting the high-speed jet wind tunnel, entering a preset Mach number closed-loop control flow, and establishing a preset Mach number sub-transonic jet flow field;
s03, collecting static pressure data of a sub-transonic jet flow field;
according to the planned measurement point positions of the jet flow uniform area, driving the four-degree-of-freedom motion mechanism to move in the XOY section of the jet flow area, and collecting the static pressure of each measurement point position
(ii) a Wherein i =1 to n, n is
The total number of measuring points in the X direction at the position, j = 1-m, m is
The total number of measurements planned in the Y direction at position,
representing coordinates of each measuring point; the four-freedom-degree motion mechanism is driven to carry out one-time independent measurement along the measurement point position of the central axis of the high-speed jet wind tunnel, and the positions of all the measurement points on the central axis are
，
Is the Y-coordinate of the central axis,
；
s04, calculating the Mach number of each measuring point;
and (3) computing the Mach number of each measuring point by using an isentropic relation, wherein the formula is as follows:
wherein the content of the first and second substances,
the total pressure of the high-speed jet wind tunnel at a preset Mach number is acquired in real time through a total pressure sensor of a wind tunnel stabilizing section in the test process;
s05, calculating the Mach number difference of each measurement point;
static pressure of measuring point position of central axis of high-speed jet wind tunnel
Obtained by
Calculating Mach number difference between Mach number of measurement points with same X coordinate and different Y coordinates and the reference value measured by the axial probe tube as the reference value, andtaking the absolute value of the difference of Mach numbers to obtain
The formula is as follows:
s06, determining jet boundary points;
calculate each
And with
Ratio of
The formula is as follows:
searching from the coordinate origin O of the high-speed jet wind tunnel in the upper and lower directions, and measuring the point position
When the first time is larger than 1%, judging that the measuring point position exceeds the jet boundary; taking the same abscissa
Is the first jet boundary point and is named
(ii) a If not present
Points > 1%, then considered absent
；
Similarly, the measuring point position of the central axis of the high-speed jet wind tunnel is searched in the upper and lower directions to obtain all jet boundary points
（
）；
S07, determining a test section uniform area of the high-speed jet wind tunnel;
respectively connected to both sides of central axis
Point, obtaining a test section uniform area with a preset Mach number;
s08, calculating a deviation value of a test section uniform area of the high-speed jet wind tunnel;
taking out the Mach number of each measurement point in the uniform area range of the test section, and calculating the Mach number distribution root mean square deviation of each measurement point
And obtaining the deviation value of the uniform area of the test section.
The method for measuring the uniform area of the subsonic jet flow field of the high-speed jet flow wind tunnel by the short-shaft probe tube is based on the characteristics that the blockage degree of the axial probe tube is small, the rigidity and the strength are sufficient, the disturbance on the subsonic flow field is small, and the method is suitable for measuring the axial (X-direction) static pressure distribution in the subsonic flow field and obtains the reference speed distribution at the central axis of the flow field by measuring the static pressure distribution at the central axis of the flow field according to the theory that the subsonic flow uniform area is the constant speed area; the four-degree-of-freedom motion mechanism of the wind tunnel model is driven to move according to the set direction and the set step length, so that the axial detecting tube integrally moves according to the set direction and the set step length, and the smaller the interval is, the more accurate the measured boundary position is; meanwhile, the measurement points along the central axis of the high-speed jet wind tunnel must be measuredA single measurement; the corresponding position of each static pressure hole on the axial detecting tube in the flow field space can be obtained after each integral movement
And measuring the static pressure at the corresponding spatial position of the jet flow field
A value; according to static pressure
The value can be calculated to obtain the flow field speed of the position; comparing the reference velocity at the central axis with the same X position
This can be determined based on the magnitude of the difference and the concept of the boundary layer
Whether the position is in a sub-transonic jet flow uniform region of the jet flow wind tunnel or not and judging the boundary position; the velocities of all the measuring points on the axial detecting tube at different positions are processed according to the method, and the boundary of the sub-transonic jet flow uniform region of the jet flow wind tunnel can be completely obtained. The method fully exerts the characteristics of small blockage degree, high rigidity and small disturbance of the convection field of the short axial detection tube under the condition of sub transonic velocity, is suitable for measuring the axial (X-direction) static pressure distribution in the sub transonic velocity flow field, reduces the disturbance of the convection field to the maximum extent, and is an efficient method for quickly and accurately measuring the boundary of the uniform region of the sub transonic velocity jet flow.
In short, the method for measuring the uniform area of the subsonic jet flow field of the high-speed jet wind tunnel by the short-axis probe tube adopts the short-axis probe tube to be installed on a four-degree-of-freedom motion mechanism which can flexibly move in the high-speed jet wind tunnel, the short-axis probe tube is driven by the four-degree-of-freedom motion mechanism to move and measure in the section of the open test section, the flow field parameters of the section of the open test section can be measured, and then the range of the uniform area of the jet flow is judged and the uniformity of the flow field of the open test section is calculated.
The method for measuring the uniform region of the sub-transonic jet flow field of the high-speed jet wind tunnel by using the short-axis probe tube is suitable for measuring the boundary and the uniformity of the uniform region of the sub-transonic jet flow field of the high-speed jet wind tunnel, the boundary of the sub-transonic jet flow uniform region is measured by using the integral movement of the short-axis probe tube, the disturbance influence on the sub-transonic jet flow field is reduced to the maximum extent, the method is simple and clear, the theoretical basis is sufficient, the boundary of the sub-transonic jet flow uniform region can be rapidly and accurately obtained, and the usable flow field range of the sub-transonic test of the high-speed jet wind tunnel is measured.
Drawings
FIG. 1 is a flow chart of a method for measuring a uniform region of a sub-transonic jet flow field of a high-speed jet wind tunnel by using a short-axis probe according to the invention;
FIG. 2 is a diagram of the range of the sub-transonic velocity flow field uniform region measured by the method for measuring the sub-transonic velocity flow field uniform region of the high-speed jet wind tunnel by using the short shaft probe.
Detailed Description
The present invention is described in detail below with reference to the drawings and examples.
Example 1
The flow chart of the method for measuring the uniform region of the sub-transonic speed jet flow field of the high-speed jet wind tunnel by using the short-axis probe tube is shown in figure 1, and the range of the measured uniform region of the sub-transonic speed jet flow field is shown in figure 2.
The high-speed jet wind tunnel consists of a gas source spherical tank, a pressure regulating valve, a stabilizing section, a spray pipe, a test chamber, an expansion section, a silencing tower and a connecting pipeline. The flow of high-pressure gas ejected from the gas source spherical tank is adjusted by controlling the opening of the pressure regulating valve, then the high-pressure gas is rectified by the stabilizing section, the spraying pipe section is accelerated, the required test flow field condition is achieved in the test chamber, and finally the high-pressure gas is discharged from the noise elimination tower through the expanding section.
The method for measuring the uniform region of the subsonic jet flow field of the high-speed jet wind tunnel by using the short shaft probe comprises the following implementation steps:
the method for measuring the uniform region of the subsonic jet flow field of the high-speed jet wind tunnel by using the short shaft probe comprises the following steps:
s01, mounting a short axial direction detection tube;
mounting a short axial detection tube on a four-degree-of-freedom motion mechanism of the high-speed jet wind tunnel, wherein the central axis of the short axial detection tube is parallel to the central axis of the high-speed jet wind tunnel; the origin of coordinates O is located at the point where the central axis of the high-speed jet wind tunnel intersects with the section of the outlet of the nozzle of the high-speed jet wind tunnel, the OX axis is located on the central axis, the forward direction along the airflow direction is the positive X direction, the Y axis is vertically upward, and the Z axis accords with the right-hand rule; the four-freedom-degree motion mechanism has X-direction freedom degrees and Y-direction freedom degrees;
s02, starting a high-speed jet wind tunnel;
starting the high-speed jet wind tunnel, entering a preset Mach number closed-loop control flow, and establishing a preset Mach number sub-transonic jet flow field;
s03, collecting static pressure data of a sub-transonic jet flow field;
according to the planned measurement point positions of the jet flow uniform area, driving the four-degree-of-freedom motion mechanism to move in the XOY section of the jet flow area, and collecting the static pressure of each measurement point position
(ii) a Wherein i =1 to n, n is
The total number of measuring points in the X direction at the position, j = 1-m, m is
The total number of measurements planned in the Y direction at position,
representing coordinates of each measuring point; the four-freedom-degree motion mechanism is driven to carry out one-time independent measurement along the measurement point position of the central axis of the high-speed jet wind tunnel, and the positions of all the measurement points on the central axis are
，
Is the central axisThe Y-direction coordinates of (a) are,
；
s04, calculating the Mach number of each measuring point;
and (3) computing the Mach number of each measuring point by using an isentropic relation, wherein the formula is as follows:
wherein, the first and the second end of the pipe are connected with each other,
the total pressure of the high-speed jet wind tunnel at a preset Mach number is acquired in real time through a total pressure sensor of a wind tunnel stabilizing section in the test process;
s05, calculating the Mach number difference of each measuring point;
static pressure of measuring point position of central axis of high-speed jet wind tunnel
Obtained by
Calculating the Mach number difference between the Mach number of the measurement points with different Y coordinates and the reference value under the same X coordinate measured by the axial probe tube as the reference value, and taking the absolute value of the Mach number difference to obtain the Mach number difference
The formula is as follows:
s06, determining jet boundary points;
calculate each
And with
Ratio of (A to B)
The formula is as follows:
searching from the coordinate origin O of the high-speed jet wind tunnel in the upper and lower directions, and measuring point positions
When the first time is larger than 1%, judging that the measuring point position exceeds the jet boundary; taking the same abscissa
Is the first jet boundary point and is named
(ii) a If not present
Points > 1%, the absence is considered
；
Similarly, the measuring point position of the central axis of the high-speed jet wind tunnel is searched in the upper and lower directions to obtain all jet boundary points
（
）；
S07, determining a test section uniform area of the high-speed jet wind tunnel;
are respectively connected withConnected to both sides of the central axis
Point, obtaining a test section uniform area with a preset Mach number;
s08, calculating a deviation value of a test section uniform area of the high-speed jet wind tunnel;
the Mach number of each measurement point in the uniform area range of the test section is taken out, and the Mach number distribution root mean square deviation of each measurement point is obtained
And obtaining the deviation value of the uniform area of the test section.
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 measuring the uniform area of the sub-transonic jet flow field of the high-speed jet wind tunnel by using the short-shaft probe is characterized by comprising the following steps of:
s01, mounting a short axial detection tube;
mounting a short axial detection tube on a four-degree-of-freedom motion mechanism of the high-speed jet wind tunnel, wherein the central axis of the short axial detection tube is parallel to the central axis of the high-speed jet wind tunnel; the origin of coordinates O is positioned at the point where the central axis of the high-speed jet wind tunnel intersects with the section of the outlet of the high-speed jet wind tunnel spray pipe, the OX axis is positioned on the central axis, the forward direction along the airflow direction is the positive X direction, the Y axis is vertically upward, and the Z axis accords with the right-hand rule; the four-freedom-degree motion mechanism has X-direction freedom degrees and Y-direction freedom degrees;
s02, starting a high-speed jet wind tunnel;
starting the high-speed jet wind tunnel, entering a preset Mach number closed-loop control flow, and establishing a preset Mach number sub-transonic jet flow field;
s03, collecting static pressure data of a sub-transonic jet flow field;
driving a four-freedom-degree motion mechanism to move in an XOY section of the jet flow region according to the planned jet flow uniform region measurement point positions, and collecting static pressure of each measurement point position
(ii) a Wherein i =1 to n, n is
The total number of measuring points in the X direction at the position, j = 1-m, m is
The total number of measurements planned in the Y direction at position,
representing coordinates of each measuring point; the four-freedom-degree motion mechanism is driven to carry out one-time independent measurement along the measurement point position of the central axis of the high-speed jet wind tunnel, and the positions of all the measurement points on the central axis are
，
Is the Y-coordinate of the central axis,
；
s04, calculating the Mach number of each measurement point;
and (3) computing the Mach number of each measuring point by using an isentropic relation, wherein the formula is as follows:
wherein the content of the first and second substances,
the total pressure of the high-speed jet wind tunnel at a preset Mach number is acquired in real time through a total pressure sensor of a wind tunnel stabilizing section in the test process;
s05, calculating the Mach number difference of each measurement point;
static pressure of measuring point position of central axis of high-speed jet wind tunnel
Obtained by
Calculating the Mach number difference between the Mach number of the measuring points with the same X coordinate and different Y coordinates and the reference value measured by the axial probe tube as the reference value, and taking the absolute value of the Mach number difference to obtain the Mach number difference
The formula is as follows:
s06, determining jet boundary points;
calculate each
And
ratio of
The formula is as follows:
searching from the coordinate origin O of the high-speed jet wind tunnel in the upper and lower directionsOf point locations
When the first time is larger than 1%, judging that the measuring point position exceeds the jet boundary; taking the same abscissa
Is the first jet boundary point and is named
(ii) a If not present
Points > 1%, the absence is considered
；
Similarly, the measuring point position of the central axis of the high-speed jet wind tunnel is searched in the upper and lower directions to obtain all jet boundary points
（
）；
S07, determining a test section uniform area of the high-speed jet wind tunnel;
connected to both sides of the central axis respectively
Point, obtaining a test section uniform area with a preset Mach number;
s08, calculating a deviation value of a test section uniform area of the high-speed jet wind tunnel;
taking out the Mach number of each measurement point in the uniform area range of the test section, and calculating the Mach number distribution root mean square deviation of each measurement point
And obtaining the deviation value of the uniform area of the test section.
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