Integrated design method and device for isolation section and transition section in supersonic wind tunnel

Abstract

The application provides an integrated design method and device for a separation section and a transition section in a supersonic wind tunnel, and the method comprises the following steps: given an inlet cross-sectional profile, a middle cross-sectional profile and an outlet cross-sectional profile; the inlet cross-sectional profile, the middle cross-sectional profile and the outlet cross-sectional profile are respectively subjected to segmentation processing; two B-spline curves respectively controlling the transition section and the separation section are generated; the inlet cross-sectional profile, the middle cross-sectional profile and the outlet cross-sectional profile are subjected to cross-sectional fusion to generate a series of fusion transition cross-sectional profiles by giving the control parameters of the two B-spline curves corresponding to each fusion transition cross section between the transition section and the separation section; and the obtained fusion transition cross-sectional profile is subjected to lofting through solidworks to obtain the final integrated profile of the separation section and the transition section. The application can match the existing rectangular or circular Laval nozzle, introduce the supersonic incoming flow to the inlet of the separation section, ensure the uniform and proper transition bending, the direction of the incoming flow does not change, and the Mach number loss is small.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the technical field of supersonic wind tunnel test device design, and particularly relates to a supersonic wind tunnel isolation section and transition section integrated design method and device. BACKGROUND

[0002] In actual engineering applications, the air inlet and the engine inlet are often offset in the air inlet layout of the aircraft using the scramjet engine, and the shape of the inlet of the scramjet engine is generally different from that of the engine inlet, the isolation section inlet is a special shape, and the Laval nozzle of the supersonic wind tunnel is often rectangular or circular.

[0003] The following problems exist when researching the variable cross-section S-shaped isolation section in the direct connection supersonic wind tunnel:

[0004] 1) The wind tunnel nozzle outlet is rectangular or circular, the isolation section inlet is a special shape, and it is difficult to connect the two;

[0005] 2) The flow condition changes after the flow passes through the connection section between the nozzle and the isolation section, and it is difficult to ensure the test effect;

[0006] 3) The conventional variable deformation turning often relies on lofting to generate, and the aerodynamic performance is poor, the total pressure loss and Mach number loss of the airflow are large, and it is difficult to meet the test requirements. SUMMARY

[0007] In view of the above technical problems existing in the prior art, the present application provides a supersonic wind tunnel isolation section and transition section integrated design method and device.

[0008] To achieve the above purpose, the technical scheme adopted by the present application is as follows:

[0009] On the one hand, the present application provides a supersonic wind tunnel isolation section and transition section integrated design method, comprising:

[0010] Given the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile, the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile correspond to the nozzle outlet, the isolation section inlet and the isolation section outlet respectively;

[0011] The inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are respectively processed in sections;

[0012] Two B-spline curves controlling the transition section and the isolation section are generated;

[0013] The inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are fused to generate a series of fusion transition cross-sectional profile lines by giving the two B-spline curve control parameters corresponding to each fusion transition cross section between the transition section and the isolation section;

[0014] The obtained fusion transition cross section profile is lofted by solidworks to obtain the final integrated profile of the isolation section and the transition section.

[0015] Further, in the two B-spline curves respectively controlling the transition section and the isolation section, the slope of the B-spline curve corresponding to the outlet section of the transition section and the inlet section of the isolation section needs to satisfy the condition of tangency.

[0016] Further, the y and z coordinates of the i-th fusion transition cross section are:

[0017] Z 1i = z j 1*(1-k1(i))+k1(i)*z j 2;

[0018] Y 1i =y j 1*(1-k1(i))+k1(i)*y j 2

[0019] Z 2i =z j 2*(1-k2(i))+k2(i)*z j 3;

[0020] Y 2i =y j 2*(1-k2(i))+k2(i)*y j 3;

[0021] wherein Z 1i , Y 1i represent the coordinate set of the z and y direction coordinates of the point of the i-th section in the transition from the inlet cross section profile to the intermediate cross section profile, Z 2i , Y 2i represent the coordinate set of the z and y direction coordinates of the point of the i-th section in the transition from the intermediate cross section profile to the outlet cross section profile. k1(i), k2(i) are the B-spline curve control parameters corresponding to the given i-th fusion transition cross section, respectively. When the inlet cross section profile, the intermediate cross section profile, and the outlet cross section profile are segmented, the inlet cross section profile, the intermediate cross section profile, and the outlet cross section profile are segmented into J sections, and the position and proportion of each section on the original profile are the same when segmented, then there are J pairs of discrete points corresponding to each other between the inlet cross section profile and the intermediate cross section profile, and there are J pairs of discrete points corresponding to each other between the intermediate cross section profile and the outlet cross section profile. Then (y j 1, z j 1), (y j 2, z j2) are the jth pair of discrete points on the entrance section profile line and the middle section profile line corresponding to each other obtained by the segmentation processing, j 2, z j 2), (y j 3, z j 3) are the jth pair of discrete points on the middle section profile line and the exit section profile line corresponding to each other obtained by the segmentation processing.

[0022] Further, the supersonic wind tunnel is a direct connection type wind tunnel, and the nozzle adopted by the direct connection type wind tunnel is a Laval nozzle. The outlet of the nozzle is rectangular or circular.

[0023] In another aspect, the present application provides a device for integrated design of a separation section and a transition section in a supersonic wind tunnel, comprising:

[0024] A first module is configured to input given entrance section profile lines, middle section profile lines and exit section profile lines, wherein the entrance section profile lines, the middle section profile lines and the exit section profile lines correspond to the outlet of the nozzle, the inlet of the separation section and the outlet of the separation section respectively;

[0025] A second module is configured to perform segmentation processing on the entrance section profile lines, the middle section profile lines and the exit section profile lines respectively;

[0026] A third module is configured to generate two B-spline curves for controlling the transition section and the separation section respectively;

[0027] A fourth module is configured to perform cross section fusion on the entrance section profile lines, the middle section profile lines and the exit section profile lines to generate a series of fusion transition section profile lines of the fusion transition sections by using the control parameters of the two B-spline curves corresponding to each fusion transition section between the transition section and the separation section;

[0028] A fifth module is configured to obtain the final integrated surface of the separation section and the transition section by lofting the obtained fusion transition section profile lines through solidworks.

[0029] In another aspect, the present application provides a computer device comprising a memory and a processor, wherein the memory stores a computer program, and the processor implements the following steps when executing the computer program:

[0030] Given entrance section profile lines, middle section profile lines and exit section profile lines, wherein the entrance section profile lines, the middle section profile lines and the exit section profile lines correspond to the outlet of the nozzle, the inlet of the separation section and the outlet of the separation section respectively;

[0031] Segmentation processing is performed on the entrance section profile lines, the middle section profile lines and the exit section profile lines respectively;

[0032] Two B-spline curves for controlling the transition section and the separation section are generated respectively;

[0033] The B-spline curve control parameters corresponding to each fusion transition section between the transition section and the isolation section are given, and the cross section fusion is performed on the inlet section line, the middle section line and the outlet section line to generate a series of fusion transition section lines of the fusion transition sections.

[0034] The final integrated surface of the isolation section and the transition section is obtained by lofting the obtained fusion transition section line through solidworks.

[0035] In another aspect, the application provides a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the following steps:

[0036] The inlet section line, the middle section line and the outlet section line are given, and the inlet section line, the middle section line and the outlet section line correspond to the nozzle outlet, the isolation section inlet and the isolation section outlet respectively.

[0037] The inlet section line, the middle section line and the outlet section line are segmented respectively.

[0038] Two B-spline curves respectively controlling the transition section and the isolation section are generated.

[0039] The B-spline curve control parameters corresponding to each fusion transition section between the transition section and the isolation section are given, and the cross section fusion is performed on the inlet section line, the middle section line and the outlet section line to generate a series of fusion transition section lines of the fusion transition sections.

[0040] The final integrated surface of the isolation section and the transition section is obtained by lofting the obtained fusion transition section line through solidworks.

[0041] Compared with the prior art, the technical effects of the application are at least embodied in the following aspects:

[0042] By using the integrated design method of the isolation section and the transition section in the supersonic wind tunnel provided by the application, the integrated surface of the isolation section and the transition section can match the existing rectangular or circular Laval nozzle, can guide the supersonic flow to the isolation section inlet, can ensure that the transition is uniformly and properly turned, the flow direction is not changed, the Mach number loss is small, and the isolation section test under variable back pressure conditions can be performed in a direct connection type wind tunnel. BRIEF DESCRIPTION OF DRAWINGS

[0043] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only show some embodiments of the application, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without any creative effort.

[0044] Figure 1 Flow chart of an embodiment of the present application;

[0045] Figure 2 Structure diagram of a direct-connect supersonic wind tunnel test device in an embodiment;

[0046] Figure 3 Diagram of given intermediate cross-sectional profile and exit cross-sectional profile in an embodiment;

[0047] Figure 4 Diagram of given entry cross-sectional profile and intermediate cross-sectional profile in an embodiment;

[0048] Figure 5 Diagram of B-spline control points;

[0049] Figure 6 Diagram of two B-spline curves satisfying a set condition in an embodiment, wherein (a) is a diagram of a first B-spline curve, and (b) is a diagram of a second B-spline curve;

[0050] Figure 7 Structure diagram of a fusion transition cross section generated in an embodiment, wherein (a) is a diagram of fusion transition from an intermediate cross section to an exit cross section, and (b) is a diagram of fusion transition from an entry cross section to an intermediate cross section. DETAILED DESCRIPTION

[0051] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0052] Referring to Figure 1 In an embodiment, an integrated design method for a separation section and a transition section in a supersonic wind tunnel is provided, comprising:

[0053] (S1) giving an entry cross-sectional profile, an intermediate cross-sectional profile, and an exit cross-sectional profile;

[0054] The entry cross-sectional profile, the intermediate cross-sectional profile, and the exit cross-sectional profile correspond to an exit of a nozzle, an entry of a separation section, and an exit of the separation section, respectively.

[0055] (S2) performing segmented processing on the entry cross-sectional profile, the intermediate cross-sectional profile, and the exit cross-sectional profile, respectively;

[0056] (S3) generating two B-spline curves for controlling the transition section and the separation section, respectively;

[0057] (S4) Through the control parameters of the two B-spline curves corresponding to each fusion transition section between the given transition section and the isolation section, the cross section fusion is performed on the inlet cross section profile, the intermediate cross section profile and the outlet cross section profile to generate a series of fusion transition section profiles of the fusion transition sections.

[0058] (S5) The obtained fusion transition section profile is lofted by solidworks to obtain the final integrated profile of the isolation section and the transition section.

[0059] The supersonic wind tunnel is a direct connection type wind tunnel, and the nozzle adopted by the direct connection type wind tunnel is a Laval nozzle, and the outlet of the Laval nozzle is rectangular or circular.

[0060] In the above step (S2), when the inlet cross section profile, the intermediate cross section profile and the outlet cross section profile are respectively segmented, the inlet cross section profile, the intermediate cross section profile and the outlet cross section profile are respectively divided into the same number of segments. Further, the proportions of the corresponding two line segments on the original profile after segmentation are approximately the same. For example, Figure 7 As shown in (a) and (b) in the drawings, the design method is to transition from the inlet cross section profile to the intermediate cross section profile, and then transition from the intermediate cross section profile to the outlet cross section profile, that is, the No. 1 line segment on the inlet cross section profile is fused and transitioned to obtain the No. 2 line segment on the intermediate cross section profile, and the No. 2 line segment on the intermediate cross section profile is fused and transitioned to obtain the No. 3 line segment on the outlet cross section profile. The proportions of the No. 1, No. 2 and No. 3 line segments on the inlet cross section profile, the intermediate cross section profile and the outlet cross section profile are approximately the same, and are discretized into equal points.

[0061] In step (S3), the shape of the b-spline curve is controlled to change the generated turning transition member, and different turning transition rules will inevitably lead to different aerodynamic performance. In actual design, the shape of the b-spline curve needs to be adjusted according to the specific profile to optimize the performance.

[0062] In step (S4), after the two b-spline curves are determined, the inlet cross section profile to the intermediate cross section profile and the intermediate cross section profile to the outlet cross section profile are fused, that is, the three profiles are fused together at one time.

[0063] Referring to Figure 2A schematic diagram of the structure of a direct-connection supersonic wind tunnel test device in one embodiment includes an air collection section (1), an airflow stabilization section (2), an integrated test section (3) of isolation and transition sections, a back pressure application device (4), and a diversion section (5). The integrated test section (3) of isolation and transition sections is the section to be designed in this invention. The integrated test section (3) of isolation and transition sections can be a variable cross-section S-shaped integrated test section of isolation and transition sections. Because the outlet of the Laval nozzle in a direct-connection wind tunnel is mostly rectangular or circular, there is a requirement for the cross-section and shape transition from the Laval nozzle to the irregular isolation section in the test. Therefore, the integrated design method of isolation and transition sections in supersonic wind tunnels provided by this invention is used to design the integrated test section (3) of isolation and transition sections, so that the airflow at the outlet of the Laval nozzle is diverted to the irregular inlet, and the incoming flow direction does not change, and the Mach number loss is small.

[0064] Reference Figure 3 and Figure 4 , Figure 3 The intermediate section profile given in one embodiment ( Figure 3 (Irregular profile in the middle), schematic diagram of the outlet section profile ( Figure 3 (circular lines in the middle); Figure 4 The inlet section profile given in one embodiment ( Figure 4 (Square profile in the middle), schematic diagram of the middle section profile ( Figure 4 (Irregular profile in the middle); the inlet cross-section profile, the middle cross-section profile, and the outlet cross-section profile correspond to the nozzle outlet, the isolation section inlet, and the isolation section outlet, respectively. The inlet cross-section profile, the middle cross-section profile, and the outlet cross-section profile are segmented to obtain a series of discrete points of the inlet cross-section profile, the middle cross-section profile, and the outlet cross-section profile, which facilitates subsequent parametric fusion.

[0065] In the design process of this invention, to avoid incoming flow loss, the most important aspect is controlling the deformation and turning. This is achieved using B-spline curves, which have strong local adjustment capabilities and can fine-tune the transition pattern of the turning curve. The B-spline curve is adjusted using four control points.

[0066] P = [0, alfa1, alfa2, 1;

[0067] [0, beta1, beta2, 1];

[0068] like Figure 5 As shown, this is a schematic diagram of the control points for the B-spline curve, where (0.0) and (1.1) are... Figure 5The coordinates of the middle point and the fifth point, which represent the given input conditions of the entrance section and the exit section of the cross section transition section of the current design, remain unchanged. In the invention, the third point is fixed at (0.5, 0.5) and remains unchanged. Alfa1 and beta1 are the horizontal and vertical coordinates of the control point 2, and alfa2 and beta2 are the horizontal and vertical coordinates of the control point 4.

[0069] Because the invention is an integrated design of the isolation section and the transition section in the supersonic wind tunnel, it is necessary to ensure that the airflow through the transition section into the isolation section is as small as possible. In order to achieve the above design purpose, when generating two B-spline curves respectively controlling the transition section and the isolation section, the slope of the B-spline curve corresponding to the exit section of the transition section and the entrance section of the isolation section needs to satisfy the tangent condition.

[0070] In an embodiment, as shown in Figure 6 alfa-a, beta-a are the horizontal and vertical coordinates of the control point a, alfa-b, beta-b are the horizontal and vertical coordinates of the control point b, alfa-c, beta-c are the horizontal and vertical coordinates of the control point c, and alfa-d, beta-d are the horizontal and vertical coordinates of the control point d. In the design, the control point coordinates of points c and d are obtained by giving the values of control points a and b through the following formula, and the design purpose is met.

[0071] alfa-a = 0.33; beta-a = 0;

[0072] alfa-b = 0.67; beta-b = 0.9;

[0073] alfa-c = 0.33; beta-c = ((1-beta-b) / (1-alfa-b))*alfa-c;

[0074] alfa-d = 0.67; beta-d = 1;

[0075] By giving the control parameters of the two B-spline curves corresponding to the i-th fusion transition section between the transition section and the isolation section, the cross section fusion of the entrance section profile, the middle section profile and the exit section profile is carried out, and the corresponding fusion transition section is generated. The y and z coordinates of the fusion transition section profile of the i-th fusion transition section are:

[0076] Z 1i = z j 1*(1-k1(i))+k1(i)*z j 2;

[0077] Y 1i = y j 1*(1-k1(i))+k1(i)*y j 2

[0078] Z 2i = z j 2*(1-k2(i))+k2(i)*z j 3;

[0079] Y 2i = y j 2*(1-k2(i))+k2(i)*y j 3;

[0080] wherein Z 1i , Y 1i represent the coordinate set of z, y direction coordinates of the point of the i-th section in the transition of the inlet section profile to the intermediate section profile, Z 2i , Y 2i represent the coordinate set of z, y direction coordinates of the point of the i-th section in the transition of the intermediate section profile to the outlet section profile. k1(i), k2(i) are respectively the B-spline curve control parameters corresponding to the given i-th fusion transition section; (y j 1, z j 1), (y j 2, z j 2), (y j 3, z j 3) respectively represent the coordinates of the discrete points on the inlet section profile, the intermediate section profile, and the outlet section profile obtained by piecewise processing.

[0081] Suppose that when the inlet section profile, the intermediate section profile, and the outlet section profile are respectively subjected to piecewise processing, the inlet section profile, the intermediate section profile, and the outlet section profile are respectively divided into J sections, and the position and proportion of each section on the original profile are the same when the section is divided, then there are J pairs of discrete points corresponding to each other between the inlet section profile and the intermediate section profile, and there are J pairs of discrete points corresponding to each other between the intermediate section profile and the outlet section profile. Then (y j 1, z j 1), (y j 2, z j 2) are the j-th pair of discrete points corresponding to each other on the inlet section profile and the intermediate section profile obtained by piecewise processing, (y j 2, z j 2), (y j 3, z j 3) are the j-th pair of discrete points corresponding to each other on the intermediate section profile and the outlet section profile obtained by piecewise processing.

[0082] Referring to Figure 7 , it is a structural schematic diagram of the fusion transition section generated in an embodiment, and finally the obtained fusion transition section profile is lofted by solidworks to obtain the integrated profile of the isolation section and the transition section.

[0083] The transition section in the application integrates the isolation section and the transition section together, is used for realizing the wind tunnel test of the special-shaped flow channel in the direct connection type wind tunnel, can adapt to the existing Laval nozzle outlet, can effectively guide the supersonic incoming flow to the special-shaped isolation section inlet, does not change the direction of the incoming flow, can prevent the loss of the incoming flow caused by the non-smooth connection and improper turning, and can realize the test of the variable cross-section special-shaped isolation section in the direct connection type wind tunnel under the condition of the counter pressure.

[0084] In an embodiment, an integrated design device of an isolation section and a transition section in a supersonic wind tunnel is provided, comprising:

[0085] A first module is configured to input a given inlet cross-sectional profile, a middle cross-sectional profile and an outlet cross-sectional profile, wherein the inlet cross-sectional profile, the middle cross-sectional profile and the outlet cross-sectional profile correspond to the nozzle outlet, the isolation section inlet and the isolation section outlet respectively;

[0086] A second module is configured to perform segmented processing on the inlet cross-sectional profile, the middle cross-sectional profile and the outlet cross-sectional profile respectively;

[0087] A third module is configured to generate two B-spline curves for controlling the transition section and the isolation section respectively;

[0088] A fourth module is configured to perform cross-sectional fusion on the inlet cross-sectional profile, the middle cross-sectional profile and the outlet cross-sectional profile to generate a series of fusion transition cross-sectional profiles by using the control parameters of the two B-spline curves corresponding to the fusion transition cross sections between the transition section and the isolation section;

[0089] A fifth module is configured to obtain the final integrated profile of the isolation section and the transition section by lofting the obtained fusion transition cross-sectional profile through solidworks.

[0090] The implementation method of each module and the construction of the model can adopt the method described in any of the foregoing embodiments, and thus will not be described here.

[0091] In another aspect, the present application provides a computer device comprising a memory and a processor, the memory storing a computer program, the processor implementing the steps of the method for integrated design of the isolation section and the transition section in a supersonic wind tunnel according to any one of the above embodiments when executing the computer program. The computer device can be a server. The computer device comprises a processor, a memory, a network interface and a database connected by a system bus. The processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operating system and the computer program in the non-volatile storage medium to run. The database of the computer device is configured to store sample data. The network interface of the computer device is configured to communicate with an external terminal through a network connection.

[0092] In another aspect, the present application provides a computer readable storage medium storing a computer program, the computer program being executed by a processor to implement the steps of the method for integrated design of the isolation section and the transition section in a supersonic wind tunnel according to any one of the above embodiments.

[0093] It is understood by a person skilled in the art that all or part of the processes in the above embodiments can be completed by a computer program instructing relevant hardware. The computer program can be stored in a non-volatile computer readable storage medium and executed to include the processes of the above embodiments. Any reference to memory, storage, database or other medium in the embodiments provided by the present application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration but not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM) and memory bus dynamic RAM (RDRAM), etc.

[0094] The details of the present application are as described above.

[0095] Any technical features in the above-described embodiments can be combined in any manner, and for the sake of brevity, not all possible combinations are described, however, any combination of the technical features is considered to be within the scope of the present specification.

[0096] The above-described embodiments are merely illustrative for the present application and are not used to limit the present application. It should be pointed out that, for those skilled in the art, some modifications and improvements can be made without departing from the concept of the present application, and these should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

[0097] The above-described embodiments are merely illustrative for the present application and are not used to limit the present application. It should be pointed out that, for those skilled in the art, some modifications and improvements can be made without departing from the concept of the present application, and these should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims. The above-described embodiments are merely illustrative for the present application and are not used to limit the present application. It should be pointed out that, for those skilled in the art, some modifications and improvements can be made without departing from the concept of the present application, and these should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. A method for integrated design of a isolator and a transition in a supersonic wind tunnel, characterized in that, The method comprises the following steps: Given the inlet section profile, the middle section profile and the outlet section profile, the inlet section profile, the middle section profile and the outlet section profile correspond to the nozzle outlet, the isolation section inlet and the isolation section outlet respectively; The inlet section profile, the middle section profile and the outlet section profile are segmented respectively; Two B-spline curves for controlling the transition section and the isolation section are generated, wherein the B-spline curves corresponding to the transition section outlet section and the isolation section inlet section need to meet the tangent condition; By using the control parameters of two B-spline curves corresponding to each fusion transition section between the transition section and the isolation section, a series of fusion transition section profiles are generated by merging the inlet section profile, the intermediate section profile, and the outlet section profile. Among these, the first... The fusion transition section profile of each fusion transition section, its The coordinates are: wherein represents a coordinate set of directional coordinates of a point of a transition section in a transition of the inlet cross-sectional profile to the intermediate cross-sectional profile represents a coordinate set of directional coordinates of a point of a transition section in a transition of the intermediate cross-sectional profile to the outlet cross-sectional profile ; and are respectively B-spline curve control parameters corresponding to a given th fusion transition section; provided that when the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are respectively subjected to piecewise processing, the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are respectively divided into pieces, and the position and proportion of each piece on the original profile are the same when the piecewise processing is performed, there are pairs of corresponding discrete points between the inlet cross-sectional profile and the intermediate cross-sectional profile, and there are pairs of corresponding discrete points between the intermediate cross-sectional profile and the outlet cross-sectional profile; then , are the th pair of discrete points on the inlet cross-sectional profile and the intermediate cross-sectional profile obtained by the piecewise processing, , are the th pair of discrete points on the intermediate cross-sectional profile and the outlet cross-sectional profile obtained by the piecewise processing;​​​ The obtained fusion transition section profile is lofted by solidworks to obtain the final integrated profile of the isolation section and the transition section.

2. The method of claim 1, wherein, The supersonic wind tunnel is a direct-connected wind tunnel, and the nozzle used in the direct-connected wind tunnel is a Laval nozzle.

3. The method of claim 2, wherein, The outlet of the nozzle is rectangular or circular.

4. An apparatus for integrated design of a isolator and a transition in a supersonic wind tunnel, characterized by, The method comprises the following steps: The first module is used for inputting the given inlet section profile, the middle section profile and the outlet section profile, wherein the inlet section profile, the middle section profile and the outlet section profile correspond to the nozzle outlet, the isolation section inlet and the isolation section outlet respectively; The second module is used for segmenting the inlet section profile, the middle section profile and the outlet section profile respectively; The third module is used for generating two B-spline curves for controlling the transition section and the isolation section, wherein the B-spline curves corresponding to the transition section outlet section and the isolation section inlet section need to meet the tangent condition; The fourth module is configured to generate a series of fusion transition section lines of the fusion transition sections by controlling parameters of two B-spline curves corresponding to each fusion transition section between the given transition section and the isolation section, and performing section fusion on the inlet section line, the intermediate section line and the outlet section line to generate the fusion transition section lines of the fusion transition sections. The coordinate of the fusion transition section line of the first fusion transition section is: The coordinate of the fusion transition section line of the first fusion transition section is: wherein represents a coordinate set of directional coordinates of a point of a transition section in a transition of the inlet cross-sectional profile to the intermediate cross-sectional profile represents a coordinate set of directional coordinates of a point of a transition section in a transition of the intermediate cross-sectional profile to the outlet cross-sectional profile are respectively B-spline curve control parameters corresponding to a given th fusion transition section; it is provided that when the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are respectively subjected to segmentation processing, the inlet cross-sectional profile, the intermediate cross-sectional profile and the outlet cross-sectional profile are respectively segmented into segments, and the position and proportion of each segment on the original profile are the same when the segmentation is performed, then there are pairs of corresponding discrete points between the inlet cross-sectional profile and the intermediate cross-sectional profile, and there are pairs of corresponding discrete points between the intermediate cross-sectional profile and the outlet cross-sectional profile; then , are the th pair of discrete points on the inlet cross-sectional profile and the intermediate cross-sectional profile obtained through segmentation processing, , are the th pair of discrete points on the intermediate cross-sectional profile and the outlet cross-sectional profile obtained through segmentation processing;​​​​ The fifth module is used for lofting the obtained fusion transition section profile by solidworks to obtain the final integrated profile of the isolation section and the transition section.

5. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that, The processor executes the computer program to realize the steps of the isolation section and the transition section integration design method in the supersonic wind tunnel according to claim 1.

6. A computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by the processor to realize the steps of the isolation section and the transition section integration design method in the supersonic wind tunnel according to claim 1.

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