CN118090124A - Wall surface step resistance evaluation test device and simulation method - Google Patents
Wall surface step resistance evaluation test device and simulation method Download PDFInfo
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Abstract
A wall surface step resistance evaluation test device and a simulation method belong to the technical field of wind tunnel tests. The wind tunnel throat cavity type pressure sensor comprises steps, a flat plate, a supporting piece and a force sensor, wherein a cavity is formed in a side wall surface of the downstream of a wind tunnel throat of an inlet section, the force sensor is arranged in the cavity, the flat plate is arranged on the force sensor through the supporting piece, the steps are arranged at the top of the flat plate, the upper surface of the flat plate is flush with the wall surface, and the flat plate is not contacted with the wall surface. The invention provides a wall surface step resistance evaluation test device and a simulation method, which are used for researching the influence rule of factors such as step height, type, installation position and the like on aerodynamic characteristics such as airflow flow characteristics, step resistance loss and the like. The resistance of different types of protrusions such as steps in turbulent flow can be directly obtained, so that the method is used for estimating the resistance of the steps in actual engineering; the method can be applied to the step flow complex working conditions in different flow rate ranges such as low speed, high speed, supersonic speed, hypersonic speed and the like, and has wider applicability.
Description
Technical Field
The invention relates to a wall surface step resistance evaluation test device and a simulation method, and belongs to the technical field of wind tunnel tests.
Background
Step flow is a classical split flow, also a common flow pattern in engineering. The front step flow has mainly three main areas: separating bubbles in front of the step, a reflow region above the step and a region after the reattachment point. In a back step flow, a vortex sequence similar to a flat shear layer is generated at the downstream of the back step, a series of vortices are generated by the upper wall and the lower wall, and as the flow is continuously generated and dissipated, the complex vortex structure is the main research object of the back step flow.
The step structure can generate significant resistance. In supersonic airflow the presence of steps also causes shock waves to interact with the boundary layer, which is the main cause of increased drag and pressure loss in the supersonic airflow. The aerodynamic drag experienced by an aircraft is mainly composed of two parts, namely differential pressure drag and frictional drag. The differential resistance can be integrated from the wall pressure, but the measurement of frictional resistance is relatively difficult. Because the step size is smaller, the influence of the wall boundary layer on the flowing around is obvious, compared with the aircraft component, the resistance value of the step is small, the current common direct measurement mode is a strain balance, but the strain balance cannot meet the measurement requirement of the small resistance value in the aspects of measurement range, sensitivity and accuracy, and the non-contact measurement mode has great difficulty in the aspects of light path arrangement, calibration correction and the like, is complex in technology and still is still immature in technical application.
Therefore, it is needed to provide a novel wall step resistance evaluation test device and a simulation method for solving the above-mentioned problems.
Disclosure of Invention
The invention provides a wall surface step resistance evaluation test device and a simulation method, which are used for researching the influence rule of factors such as step height, type, installation position and the like on aerodynamic characteristics such as airflow flow characteristics, step resistance loss and the like. The invention is developed to solve the problem that a strain balance cannot meet the measurement requirement of small resistance in terms of measurement range, sensitivity and accuracy, but a noncontact measurement mode has great difficulty in terms of light path arrangement, calibration correction and the like, and a brief overview of the invention is given below to provide basic understanding of certain 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.
The technical scheme of the invention is as follows:
According to the scheme I, the wall step resistance evaluation test device comprises steps, a flat plate, a supporting piece and a force sensor, wherein a cavity is formed in one side wall surface of the downstream of a wind tunnel throat of an inlet section, the force sensor is arranged in the cavity, the flat plate is arranged on the force sensor through the supporting piece, the step is arranged at the top of the flat plate, the upper surface of the flat plate is flush with the wall surface, and the flat plate is not contacted with the wall surface.
Preferably: gaps h are reserved between the periphery of the flat plate and the wall surface, and the gaps h are 0.3-0.5 mm.
The second scheme is a wall step resistance evaluation test simulation method, which is realized by the wall step resistance evaluation test device according to the first scheme, and comprises the following steps:
s1, connecting the lower surface of a flat plate with a supporting piece, connecting the supporting piece with a force sensor, and arranging the force sensor and the flat plate in a cavity;
S2, designing a step geometric parameter, and giving an incoming flow pneumatic parameter and the local boundary layer thickness delta at the step, namely calculating the boundary layer development distance x required by the local boundary layer thickness delta at the pre-installation step according to a flat turbulence boundary layer thickness calculation formula;
S3, starting the wind tunnel, and collecting the axial force of the flat plate during step-free installation through the force sensor after the flow field is stable;
mounting a step on the rear half part of the flat plate, wherein the axial length of the step is not more than half of the whole length of the flat plate;
The local boundary layer thickness delta at the step starts from the wind tunnel throat, and the required boundary layer development distance x consists of the length of the tunnel wall and a section of flat plate length of the step front edge, namely the boundary layer development distance x corresponding to the local Leinox number at the step front edge;
Under the condition of the same wind tunnel flow field, the steps are arranged on the flat plate, and the axial force of the flat plate added with the steps is collected through the force sensor, namely, the axial force of the flat plate is obtained when the steps are arranged;
s4, calculating the difference between the axial force of the flat plate when the step is installed and the axial force of the flat plate when the step is not installed, and obtaining the step self-resistance data of the unit span-wise width through data correction.
Preferably: the given incoming flow aerodynamic parameters in S2 include mach number Ma, total pressure P 0, and total temperature T 0;
Calculating local Reynolds number of boundary layer development distance x corresponding to installation position of step on flat plate The following formula:
Formula (1.1)
Then according to the calculation formula of the thickness of the plate turbulence boundary layer, the local Reynolds number is calculatedThe corresponding boundary layer development distance x, which is the length required by the local boundary layer thickness, is as follows:
equation (1.2).
Preferably: the turbulent boundary layer of the step is realized by attaching a transition strap at the front edge and at the inlet of the wind tunnel throat.
Preferably: the specific steps of the data correction in S4 are as follows:
S2.1, in order to obtain step self-resistance data D of unit spanwise width, calculating through CFD flow fields, respectively obtaining an axial force calculation value N1 without a three-dimensional effect in the CFD flow field of the flat plate without step installation, an axial force calculation value M1 with a three-dimensional boundary effect in the CFD flow field of the flat plate without step installation, an axial force calculation value N2 without a three-dimensional effect in the CFD flow field of the flat plate with step installation and an axial force calculation value M2 with a three-dimensional boundary effect in the CFD flow field of the flat plate with step installation under each test working condition;
S2.2, obtaining a resistance influence quantity M3 with three-dimensional boundary effect in the CFD flow field of the flat plate during the step-free installation according to the axial force calculated value N1 without the three-dimensional effect in the CFD flow field of the flat plate during the step-free installation and the axial force calculated value M1 with the three-dimensional boundary effect in the CFD flow field of the flat plate during the step-free installation, wherein M3=N1-M1;
S2.3, according to an axial force calculated value N2 without a three-dimensional effect in the CFD flow field of the flat plate with the step installation and an axial force calculated value M2 with a three-dimensional boundary effect in the CFD flow field of the flat plate with the step installation, obtaining a resistance influence quantity M4 with the three-dimensional boundary effect of the flat plate with the step installation, wherein M4=N2-M2, and further obtaining a resistance ratio lambda, lambda= (N2-N1)/N2 of the step resistance without the three-dimensional boundary effect in the CFD flow field and the flat plate with the step installation;
S2.4, obtaining a test axial force T1 with a three-dimensional boundary effect of the flat plate without the step installation and a test axial force T2 with a three-dimensional boundary effect of the flat plate with the step installation through tests, thereby obtaining test resistance T3 without the three-dimensional boundary effect of the flat plate in the tests, T3=T1-M3 and test resistance T4 without the three-dimensional boundary effect of the flat plate with the step installation in the tests, T4=T2-M4,
S2.5, the correction quantity K without the three-dimensional boundary effect is adjusted through a test, so that the resistance X without the three-dimensional boundary effect of the step can be obtained, and the resistance X is as follows:
K=（T4-T3）/T4
Kλ=X/（T2-M4）
The following steps are obtained:
X=λ[（T2-T1）-（M2-M1）+（N2-N1）]
And finally, obtaining the self-resistance data D of the step of the unit width in the expanding direction, wherein D=X/W, W is the expanding direction width of the step, and the obtained self-resistance data D of the step of the unit width in the expanding direction is used for estimating the resistance of the step in the actual engineering.
Preferably: the test method for collecting the axial force of the flat plate through the force sensor in the step S3 is as follows:
S3.1, carrying out a flat plate test of step-free installation under the Mach number Ma of the wind tunnel incoming flow, and attaching a transition tape on the wind tunnel wall surface before the inlet of the wind tunnel throat to realize manual transition;
S3.2, mach number Ma is regulated by a flowmeter arranged in a vacuum pipeline, mach number Ma is calculated by the along-path static pressure and the atmospheric pressure of a wind tunnel inlet and fed back to a measurement and control system until the Mach number Ma is regulated to a required Mach number Ma;
S3.3, after the flow field of the required Mach number Ma is established, measuring the transition condition of the boundary layer of the wind tunnel inlet by an infrared thermal imaging method, and judging whether the wall surface of the wind tunnel is completely transited;
s3.4, measuring a speed field of the step front edge area by PIV technology, and determining the thickness of a boundary layer at the step front edge area;
s3.5, after the flow field of the required Mach number Ma is established, measuring the axial force born by the flat plate during step-free installation through the force sensor;
S3.6, after the step is arranged on the flat plate, carrying out a flat plate test when the step is arranged under the Mach number Ma of the wind tunnel, spreading a transition tape on the wall surface of the wind tunnel before the inlet of the throat of the wind tunnel, realizing manual transition, and repeating the steps S3.2-S3.5 to obtain the axial force of the step on the flat plate.
The invention has the following beneficial effects:
1. the invention can directly obtain the resistance of different types of projections such as steps in turbulent flow, thereby being used for estimating the resistance of the steps in actual engineering;
2. The invention can be applied to the complicated step flow working conditions in different flow speed ranges such as low speed, high speed, supersonic speed, hypersonic speed and the like, is used for researching the influence rules of factors such as step height, type, installation position and the like on the aerodynamic characteristics such as airflow flow characteristics, step resistance loss and the like, and has wider applicability.
Drawings
FIG. 1 is a schematic view of a wall step resistance evaluation test apparatus;
FIG. 2 is a mating installation view of the flat plate and the step of the present invention;
in the figure, the device comprises a 1-step, a 2-flat plate, a 3-supporting piece, a 4-force sensor, a 5-cavity, a 6-wall surface, a 7-wind tunnel throat and an 8-inlet section.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the present invention is divided into a fixed connection and a detachable connection, wherein the fixed connection (i.e. the non-detachable connection) includes, but is not limited to, a conventional fixed connection manner such as a hemmed connection, a rivet connection, an adhesive connection, a welded connection, etc., and the detachable connection includes, but is not limited to, a conventional detachable manner such as a threaded connection, a snap connection, a pin connection, a hinge connection, etc., and when the specific connection manner is not specifically limited, at least one connection manner can be found in the existing connection manner by default, so that the function can be realized, and a person skilled in the art can select the connection according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
The first embodiment is as follows: referring to fig. 1-2, a wall step resistance evaluation test device of the present embodiment is described, including a step 1, a flat plate 2, a support 3 and a force sensor 4, a cavity 5 is processed on a side wall 6 downstream of a wind tunnel throat 7 of an inlet section 8, the force sensor 4 is disposed in the cavity 5, the flat plate 2 is mounted on the force sensor 4 through the support 3, the top of the flat plate 2 is provided with the step 1, that is, the force sensor 4 and the flat plate 2 are sealed in the cavity 5, the upper surface of the flat plate 2 is flush with the wall 6, the flat plate 2 is not in contact with the wall 6, and the gap between the wall 6 and the flat plate 2 is communicated with the wind tunnel. By monitoring the front and rear pressure of the cavity, it is ensured that the cavity pressure is stable, no flow, no pressure difference between the wind tunnel above the plate 2 and the cavity 5 below.
The turbulent boundary layer of the step 1 is realized by attaching a transition tape at the front edge and at the inlet of the wind tunnel throat 7.
Gaps h are reserved between the periphery of the flat plate 2 and the wall surface 6, and the gaps h are 0.3-0.5 mm, so that redundant force generated by the force sensor 4 in other directions is reduced, and the measurement influence on the resistance direction is eliminated. The step 1 is arranged at the rear half part of a section of flat plate 2, the transverse widths of the flat plate 2 and the step 1 are slightly smaller, and the axial length of the step 1 is not more than half of the whole length of the flat plate 2.
The second embodiment is as follows: referring to fig. 1-2, a wall step resistance evaluation test device according to a specific embodiment of the present embodiment is described, and a wall step resistance evaluation test simulation method according to the present embodiment is a test method for developing a step 1 resistance measurement study based on a force measurement test technique in a conventional wind tunnel and in combination with a step 1 resistance measurement feature.
The flow around the step 1 is complex, the flow has three-dimensional characteristics, and the flow in front of the step 1 is simplified into two-dimensional flat plate 2 turbulent flow for the convenience of carrying out experiments.
The method specifically comprises the following steps:
s1, connecting the lower surface of a flat plate 2 with a supporting piece 3, connecting the supporting piece 3 with a force sensor 4, and arranging the force sensor 4 and the flat plate 2 in a cavity 5;
S2, designing geometric parameters of the step 1, and calculating a boundary layer development distance x required by pre-installing the local boundary layer thickness delta at the step 1 by giving an incoming flow pneumatic parameter and the local boundary layer thickness delta at the step 1, namely according to a calculation formula of the turbulent boundary layer thickness of the flat plate 2;
S3, starting the wind tunnel, and collecting the axial force of the flat plate 2 during the installation of the step-free 1 through the force sensor 4 after the flow field is stable;
Mounting a step 1 on the rear half part of the flat plate 2, wherein the axial length of the step 1 is not more than half of the whole length of the flat plate 2;
The local boundary layer thickness delta at the step 1 starts from the wind tunnel throat 7, and the required boundary layer development distance x consists of the length of the tunnel wall and the length of a section of flat plate 2 at the front edge of the step 1, namely the boundary layer development distance x corresponding to the local Leinox number at the front edge of the step 1;
Under the condition of the same wind tunnel flow field, the step 1 is arranged on the flat plate 2, and the force sensor 4 is used for collecting the axial force of the flat plate 2 added with the step 1, namely the axial force of the flat plate 2 when the step 1 is arranged;
S4, calculating the difference between the axial force of the flat plate 2 when the step 1 is installed and the axial force of the flat plate 2 when the step 1 is not installed, and obtaining the self resistance data of the step 1 with unit span-wise width through data correction.
The given incoming flow aerodynamic parameters in S2 include mach number Ma, total pressure P 0, and total temperature T 0;
Calculating the local Reynolds number of the boundary layer development distance x corresponding to the installation position of the step 1 on the flat plate 2 The following formula:
Formula (1.1)
Then according to the calculation formula of the thickness of the turbulent boundary layer of the flat plate 2, the local Reynolds number is calculatedThe corresponding boundary layer development distance x, which is the length required by the local boundary layer thickness, is as follows:
equation (1.2).
The thickness of the boundary layer at the front edge of the step 1 is a turbulent boundary layer, and the transition tape is attached at the inlet of the wind tunnel throat 7.
The specific steps of the data correction in S4 are as follows:
S2.1, in order to obtain step self-resistance data D of unit spanwise width, calculating through CFD flow fields, respectively obtaining an axial force calculation value N1 without three-dimensional effect in the CFD flow field of the flat plate 2 without step 1 installation, an axial force calculation value M1 with three-dimensional boundary effect in the CFD flow field of the flat plate 2 without step 1 installation, an axial force calculation value N2 without three-dimensional effect in the CFD flow field of the flat plate 2 with step 1 installation and an axial force calculation value M2 with three-dimensional boundary effect in the CFD flow field of the flat plate 2 with step 1 installation under each test working condition;
s2.2, obtaining a resistance influence quantity M3 with three-dimensional boundary effect in the CFD flow field of the flat plate 2 when the flat plate 1 is installed without the step 1 according to an axial force calculated value N1 without the three-dimensional effect in the CFD flow field of the flat plate 2 when the flat plate 1 is installed without the step 1 and an axial force calculated value M1 with the three-dimensional boundary effect in the CFD flow field of the flat plate 2 when the flat plate 1 is installed without the step 1, wherein M3=N1-M1;
S2.3, according to an axial force calculated value N2 without a three-dimensional effect in the CFD flow field of the flat plate 2 when the step 1 is installed and an axial force calculated value M2 with a three-dimensional boundary effect in the CFD flow field of the flat plate 2 when the step 1 is installed, obtaining a resistance influence quantity M4 with the three-dimensional boundary effect of the flat plate 2 when the step 1 is installed, wherein M4=N2-M2, and further obtaining a resistance ratio lambda, lambda= (N2-N1)/N2 of the step resistance without the three-dimensional boundary effect in the CFD flow field and the flat plate 2 when the step 1 is installed;
S2.4, obtaining a test axial force T1 without a three-dimensional boundary effect of the flat plate 2 when the step 1 is installed and a test axial force T2 with a three-dimensional boundary effect of the flat plate 2 when the step 1 is installed through tests, thereby obtaining test resistance T3 without a three-dimensional boundary effect of the flat plate 2 in the tests, T3=T1-M3 and test resistance T4 without a three-dimensional boundary effect of the flat plate 2 when the step 1 is installed in the tests, T4=T2-M4,
S2.5, the correction quantity K without the three-dimensional boundary effect is adjusted through a test, so that the resistance X without the three-dimensional boundary effect of the step can be obtained, and the resistance X is as follows:
K=（T4-T3）/T4
Kλ=X/（T2-M4）
The following steps are obtained:
X=λ[（T2-T1）-（M2-M1）+（N2-N1）]
And finally, obtaining the self-resistance data D of the step of the unit width in the expanding direction, wherein D=X/W, W is the expanding direction width of the step, and the obtained self-resistance data D of the step of the unit width in the expanding direction is used for estimating the resistance of the step in the actual engineering.
The test method for collecting the axial force of the flat plate 2 through the force sensor 4 in the step S3 is as follows:
s3.1, carrying out a flat plate 2 test of step-free installation under the Mach number Ma of the wind tunnel incoming flow, and attaching a transition tape on the wind tunnel wall surface 6 before the inlet of the wind tunnel throat 7 in a direction of stretching to realize manual transition;
S3.2, mach number Ma is regulated by a flowmeter arranged in a vacuum pipeline, mach number Ma is calculated by the along-path static pressure and the atmospheric pressure of a wind tunnel inlet and fed back to a measurement and control system until the Mach number Ma is regulated to a required Mach number Ma;
S3.3, after the flow field of the required Mach number Ma is established, measuring the transition condition of the boundary layer of the wind tunnel inlet by an infrared thermal imaging method, and judging whether the wind tunnel wall surface 6 is completely transited;
s3.4, measuring a speed field of the step front edge area by PIV technology, and determining the thickness of a boundary layer at the step front edge area;
S3.5, after the flow field of the required Mach number Ma is established, measuring the axial force born by the flat plate 2 during the installation of the step-free 1 through the force sensor 4;
S3.6, collecting the axial force of the flat plate 2 added with the step 1 through the force sensor 4: after the step 1 is installed on the flat plate 2, a flat plate 2 test is carried out under the Mach number Ma of the wind tunnel when the step 1 is installed, the wind tunnel wall surface 6 before the inlet of the wind tunnel throat 7 is spread to attach a transition tape, so that manual transition is realized, in order to ensure data reliability, the steps S3.2-S3.5 are repeated for at least 3-5 times, and the data are averaged to obtain the axial force of the step 1 on the flat plate 2.
It should be noted that, in the above embodiments, as long as the technical solutions that are not contradictory can be arranged and combined, those skilled in the art can exhaust all the possibilities according to the mathematical knowledge of the arrangement and combination, so the present invention does not describe the technical solutions after the arrangement and combination one by one, but should be understood that the technical solutions after the arrangement and combination have been disclosed by the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The wall step resistance evaluation test device is characterized in that: including step (1), dull and stereotyped (2), support piece (3) and force sensor (4), processing has cavity (5) on a side wall (6) of the wind-tunnel throat (7) low reaches of inducer (8), is provided with force sensor (4) in cavity (5), and dull and stereotyped (2) are installed on force sensor (4) through support piece (3), and dull and stereotyped (2) top is provided with step (1), dull and stereotyped (2) upper surface flushes with wall (6), and does not contact between dull and stereotyped (2) and the wall (6).
2. The wall step resistance evaluation test device according to claim 1, wherein: gaps h are reserved between the periphery of the flat plate (2) and the wall surface (6), and the gaps h are 0.3-0.5 mm.
3. The wall step resistance evaluation test simulation method is realized by the wall step resistance evaluation test device according to claim 2, and is characterized by comprising the following steps:
s1, connecting the lower surface of a flat plate (2) with a supporting piece (3), connecting the supporting piece (3) with a force sensor (4), and arranging the force sensor (4) and the flat plate (2) in a cavity (5);
s2, designing geometric parameters of the step (1), and giving the incoming flow pneumatic parameters and the local boundary layer thickness delta at the step (1), namely calculating the boundary layer development distance x required by the local boundary layer thickness delta at the pre-installation step (1) according to a calculation formula of the turbulent boundary layer thickness of the flat plate (2);
S3, starting the wind tunnel, and collecting the axial force of the flat plate (2) during the installation of the step-free plate (1) through the force sensor (4) after the flow field is stable;
mounting a step (1) on the rear half part of the flat plate (2), wherein the axial length of the step (1) is not more than half of the whole length of the flat plate (2);
the local boundary layer thickness delta at the step (1) starts from the wind tunnel throat (7), and the required boundary layer development distance x consists of the length of the tunnel wall and the length of a section of flat plate (2) at the front edge of the step (1), namely the boundary layer development distance x corresponding to the local Raney number at the front edge of the step (1);
Under the condition of the same wind tunnel flow field, the step (1) is arranged on the flat plate (2), and the force sensor (4) is used for collecting the axial force of the flat plate (2) plus the step (1), namely the axial force of the flat plate (2) when the step (1) is arranged;
S4, calculating the difference between the axial force of the flat plate (2) when the step (1) is installed and the axial force of the flat plate (2) when the step (1) is not installed, and obtaining the self resistance data of the step (1) with unit span width through data correction.
4. A wall step resistance evaluation test simulation method according to claim 3, wherein: the given incoming flow aerodynamic parameters in S2 include mach number Ma, total pressure P 0, and total temperature T 0;
Calculating the local Reynolds number of the boundary layer development distance x corresponding to the installation position of the step (1) on the flat plate (2) The following formula:
Formula (1.1)
Then according to the calculation formula of the thickness of the turbulent boundary layer of the flat plate (2), the local Reynolds number is calculatedThe corresponding boundary layer development distance x, which is the length required by the local boundary layer thickness, is as follows:
equation (1.2).
5. The simulation method for wall step resistance evaluation test according to claim 4, wherein: the turbulent boundary layer of the step (1) is at the front edge, and a transition tape is attached to the inlet of the wind tunnel throat (7).
6. The simulation method for wall step resistance evaluation test according to claim 5, wherein: the specific steps of the data correction in S4 are as follows:
S2.1, in order to obtain step self-resistance data D of unit spanwise width, calculating through CFD flow fields, respectively obtaining an axial force calculation value N1 without three-dimensional effect in the CFD flow field of the flat plate (2) without step (1) during installation, an axial force calculation value M1 with three-dimensional boundary effect in the CFD flow field of the flat plate (2) without step (1) during installation, an axial force calculation value N2 without three-dimensional effect in the CFD flow field of the flat plate (2) with step (1) during installation and an axial force calculation value M2 with three-dimensional boundary effect in the CFD flow field of the flat plate (2) with step (1) during installation under each test working condition;
S2.2, obtaining a resistance influence quantity M3 with three-dimensional boundary effect in the CFD flow field of the flat plate (2) when the flat plate (1) is installed according to an axial force calculated value N1 without three-dimensional effect in the CFD flow field of the flat plate (2) when the flat plate (1) is installed and an axial force calculated value M1 with three-dimensional boundary effect in the CFD flow field of the flat plate (2) when the flat plate (1) is installed, wherein M3=N1-M1;
S2.3, according to an axial force calculated value N2 without a three-dimensional effect in the CFD flow field of the flat plate (2) when the step (1) is installed and an axial force calculated value M2 with a three-dimensional boundary effect in the CFD flow field of the flat plate (2) when the step (1) is installed, obtaining a resistance influence quantity M4 with the three-dimensional boundary effect of the flat plate (2) when the step (1) is installed, wherein M4=N2-M2, and further obtaining a resistance ratio lambda, lambda= (N2-N1)/N2 of the step resistance without the three-dimensional boundary effect in the CFD flow field and the flat plate (2) when the step (1) is installed;
S2.4, obtaining a test axial force T1 with a three-dimensional boundary effect of the flat plate (2) without the step (1) during installation and a test axial force T2 with a three-dimensional boundary effect of the flat plate (2) with the step (1) during installation through tests, thereby obtaining test resistance T3 without the three-dimensional boundary effect of the flat plate (2) during the tests, T3=T1-M3 and test resistance T4 without the three-dimensional boundary effect of the flat plate (2) during the installation of the step (1) during the tests, T4=T2-M4,
S2.5, the correction quantity K without the three-dimensional boundary effect is adjusted through a test, so that the resistance X without the three-dimensional boundary effect of the step can be obtained, and the resistance X is as follows:
K=（T4-T3）/T4
Kλ=X/（T2-M4）
The following steps are obtained:
X=λ[（T2-T1）-（M2-M1）+（N2-N1）]
And finally, obtaining the self-resistance data D of the step of the unit width in the expanding direction, wherein D=X/W, W is the expanding direction width of the step, and the obtained self-resistance data D of the step of the unit width in the expanding direction is used for estimating the resistance of the step in the actual engineering.
7. The wall step resistance evaluation test simulation method according to claim 6, wherein: the test method for collecting the axial force of the flat plate (2) through the force sensor (4) in the step S3 is as follows:
S3.1, carrying out a flat plate (2) test of step-free installation under the Mach number Ma of the wind tunnel incoming flow, and carrying out manual transition by spreading and attaching a transition tape on a wind tunnel wall surface (6) in front of an inlet of a wind tunnel throat (7);
S3.2, mach number Ma is regulated by a flowmeter arranged in a vacuum pipeline, mach number Ma is calculated by the along-path static pressure and the atmospheric pressure of a wind tunnel inlet and fed back to a measurement and control system until the Mach number Ma is regulated to a required Mach number Ma;
S3.3, after the flow field of the required Mach number Ma is established, measuring the transition condition of the boundary layer of the wind tunnel inlet by an infrared thermal imaging method, and judging whether the wind tunnel wall surface (6) is completely transited;
s3.4, measuring a speed field of the step front edge area by PIV technology, and determining the thickness of a boundary layer at the step front edge area;
s3.5, after the flow field of the required Mach number Ma is established, measuring the axial force born by the flat plate (2) during the installation of the step-free plate (1) through the force sensor (4);
S3.6, after the step (1) is installed on the flat plate (2), carrying out a flat plate (2) test when the step (1) is installed under the Mach number Ma of the wind tunnel incoming flow, and applying transition tape to the wind tunnel wall surface (6) before the inlet of the wind tunnel throat (7) in a spreading way to realize manual transition, and repeating the steps S3.2-S3.5 to obtain the axial force of the step (1) on the flat plate (2).
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