CN111006836A - Tandem supersonic and hypersonic wind tunnel and flow stabilizing method thereof - Google Patents
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Abstract
本发明公开了一种串列式超声速及高超声速风洞及其稳流方法，属于串列式超声速及高超声速低湍流度风洞及静风洞设计领域，通过将多孔材料置于串列式超声速及高超声速风洞的安定段内，可以在不破坏流场结构的同时对声波、涡波和熵波这些扰动波进行一部分的吸收，同时多孔材料具有较强的结构强度，可以在较大马赫数范围内承受超声速及高超声速风洞中产生的强激波冲击而内部结构不被破坏。将多孔材料垂直置于串列式超音速风洞的安定段中时，多孔材料构成的主体吸收流场扰动，减弱激波强度，将流动分离产生的大分离涡进行过滤，进而提高超声速及高超声速风洞试验段入口的流场均匀度，提升风洞实验的可信度。
The invention discloses a tandem supersonic and hypersonic wind tunnel and a flow stabilization method thereof, belonging to the design field of tandem supersonic and hypersonic low-turbulence wind tunnels and static wind tunnels. In the stable section of supersonic and hypersonic wind tunnels, the perturbation waves such as acoustic waves, vortex waves and entropy waves can be partially absorbed without destroying the flow field structure. It can withstand strong shock waves generated in supersonic and hypersonic wind tunnels within the Mach number range without damage to the internal structure. When the porous material is placed vertically in the stable section of the tandem supersonic wind tunnel, the main body composed of the porous material absorbs the disturbance of the flow field, weakens the shock wave intensity, and filters the large separation vortices generated by the flow separation, thereby increasing the supersonic speed and high speed. The uniformity of the flow field at the entrance of the supersonic wind tunnel test section improves the reliability of the wind tunnel test.
Description
Technical Field
The invention belongs to the field of tandem supersonic and hypersonic low-turbulence wind tunnels and static wind tunnels, and particularly relates to a tandem supersonic and hypersonic wind tunnel based on porous material flow control and a flow stabilizing method thereof.
Background
In the aspect of aerodynamic force, a plurality of unsolved problems exist at present, such as the problem of boundary layer stability and transition of hypersonic flow, the problems of flow separation and reattachment, the real gas effect and shock wave/boundary layer interference, and the like, which directly influence the aerodynamic, control and thermal protection design of the hypersonic and hypersonic aircraft. The ground wind tunnel test is a main way for developing supersonic speed and hypersonic speed aerodynamic research. The Ludwieg tube wind tunnel is a hypersonic wind tunnel facility with the most economic benefit so far, and if the conventional Ludwieg tube wind tunnel wants to realize a relatively large-size test section with supersonic flow, the conventional Ludwieg tube wind tunnel needs to be arranged in a serial mode, and an additional spray pipe and a stabilizing section are introduced. However, the introduction of external elements limits mass flow, and causes strong shock wave effect and large flow separation, which destroys the uniformity of the flow field in the supersonic and hypersonic wind tunnel test section. Therefore, different types of damping materials need to be arranged in the stabilizing section to improve the flow quality and ensure the reliability of the wind tunnel experiment.
In the aspect of steady flow of a wind tunnel flow field, a porous plate, a honeycomb plate, a steel wire mesh and an air filter are mostly adopted as damping materials. Among these damping materials, the perforated plates and the honeycomb plates have a rather strong body, which can weaken flow separation and filter the direct flow, but which itself can cause additional turbulence; the steel wire mesh and the air filter are easily corroded, and the effect is not obvious when shock waves and complex flow exist.
Disclosure of Invention
Aiming at the defects or improvement requirements of the prior art, the invention provides a tandem supersonic and hypersonic wind tunnel and a flow stabilizing method thereof, so that the technical problem of poor incoming flow quality of a second spray pipe of the conventional tandem wind tunnel is solved.
To achieve the above object, according to an aspect of the present invention, there is provided a flow stabilizing method for a tandem supersonic and hypersonic wind tunnel, comprising:
placing a porous material in a stabilizing section, wherein the pore thickness of the porous material disposed upstream of the stabilizing section is greater than the pore thickness of the porous material subsequently disposed.
Preferably, the porous material is arranged vertically along the axis of the stabilizing section, and the diameter of the porous material is consistent with the diameter of the stabilizing section.
Preferably, the pore diameter of the porous material is 0.05 mm-2 mm.
Preferably, the porosity of the porous material is 70% to 96%.
Preferably, the porous material has a permeability of 1 × 10-9m2～1×10-5m2。
According to another aspect of the present invention, there is provided a tandem supersonic and hypersonic wind tunnel comprising: the device comprises a first spray pipe, a stabilizing section, a second spray pipe and a testing section;
placing a porous material in the stabilizing section, wherein the pore thickness of the porous material disposed upstream of the stabilizing section is greater than the pore thickness of the porous material subsequently disposed.
Preferably, the porous material is arranged vertically along the axis of the stabilizing section, and the diameter of the porous material is consistent with the diameter of the stabilizing section.
Preferably, the pore diameter of the porous material is 0.05 mm-2 mm.
Preferably, the porosity of the porous material is 70% to 96%.
Preferably, the porous material has a permeability of 1 × 10-9m2～1×10-5m2。
In general, compared with the prior art, the above technical solution contemplated by the present invention can achieve the following beneficial effects:
(1) perforated plates, honeycomb plates, steel wire meshes or air filters are generally used in the existing wind tunnel stabilizing section, and in the damping materials, the perforated plates and the honeycomb plates can cause additional vortex; in the presence of shock waves and large flow separations, steel wire meshes and conventional screens are not very effective in stabilizing the flow. The porous material is provided with micropore gaps, so that the disturbance waves such as sound waves, vortex waves and entropy waves can be partially absorbed while the flow field structure is not damaged, and meanwhile, the porous material has strong structural strength and can bear the strong shock wave impact generated in the supersonic speed and hypersonic speed wind tunnel within a large Mach number range, and the internal structure is not damaged. When the porous material is vertically arranged in the stable section of the tandem supersonic wind tunnel, a main body formed by the porous material absorbs flow field disturbance, weakens shock wave intensity, and filters large separation vortex generated by flow separation, so that the flow field uniformity of an entrance of a supersonic and hypersonic wind tunnel test section is improved, the technical problem that the incoming flow quality of a second spray pipe of the existing tandem wind tunnel is poor is solved, and the reliability of a wind tunnel test is improved;
(2) the technical problem caused by the fact that the porous metal materials with different properties such as permeability, porosity and the like have different flow stabilizing effects on the wind tunnel, and parameter selection errors can cause the situation that the flow stabilizing effect is poor and even the wind tunnel cannot normally run is solved. In order to overcome the difficulties, the invention carries out series parameter research by a numerical simulation method of the supersonic velocity and hypersonic velocity wind tunnel of the tandem nozzle, and determines the parameter range of the porous metal material for effectively improving the inflow quality of the wind tunnel. The overall size of the porous material is determined by the size of the calming section. For the wind tunnel stabilizing section with the conventional size, the aperture of the porous material is 0.05 mm-2 mm, the porosity is 70% -96%, and the permeability is 1 multiplied by 10-9m2～1×10-5m2. Proper parameter selection has good effect on eliminating the incoming flow disturbance in the stabilizing section, and the experimental flow field quality of the supersonic speed and the hypersonic speed of the tandem spray pipe can be improved.
Drawings
FIG. 1 is a schematic diagram of a method for stabilizing the flow of a porous material at a stabilizing section of a supersonic and hypersonic wind tunnel with tandem nozzles according to an embodiment of the invention;
FIG. 2 is a mach number distribution diagram of a supersonic and hypersonic wind tunnel with tandem nozzles for flow stabilization without porous materials according to an embodiment of the present invention;
FIG. 3 is a mach number distribution diagram of a supersonic and hypersonic wind tunnel with a tandem nozzle for stabilizing flow of porous material according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
According to the invention, the flow stabilizing effect of the porous material is researched according to the aerodynamic characteristics, the porous material is arranged in the stabilizing section of the tandem supersonic and hypersonic wind tunnel, and the main body formed by the porous material absorbs flow field disturbance and weakens incoming flow unevenness caused by the flow field disturbance, so that the flow field quality of the wind tunnel test section inlet is improved, the effect of high-efficiency flow stabilization of the tandem supersonic and hypersonic Ludwieg tube wind tunnel is realized, and the effect of improving the incoming flow quality of the tandem supersonic and hypersonic wind tunnel test section is achieved.
When the air flow passes through the porous damping material, the large-scale vortex structure and disturbance of the air flow can be damaged, the flow of the air flow can be uniform, and the flow field pulsation can be reduced. The arrangement of the porous materials is reasonably designed, and the thicker porous metal materials are vertically arranged at the upstream of the stabilizing section to bear the impact load of the incoming flow, so that the large flow separation is damaged; then, a porous medium material with smaller pores is used for further refining the vortex structure; finally, the purposes of uniform flow, turbulence reduction and noise reduction are realized.
Example 1
The junction of example 1 is shown in FIG. 1And (6) patterning. In embodiment 1 of fig. 1, two porous materials are arranged in the stabilizing section of the serial nozzle supersonic and hypersonic wind tunnel for stabilizing the flow, the porous material is made of metal-based materials such as foamed aluminum and the like, so that the porous damping plate has enough strength to resist strong impact generated by the first nozzle, the pore diameter of the porous material is 0.05-2 mm, the porosity is 70-96%, and the permeability is 1 × 10-9m2～1×10-5m2And the normal operation of the wind tunnel is not influenced on the premise that the porous damping plate realizes a good flow stabilizing effect.
In the embodiment of the invention, the number of the blocks of the porous material arranged along the axis of the stabilizing section is not limited to two, preferably 1-3, and can be determined according to actual needs, and the embodiment of the invention is not limited uniquely.
By means of a numerical calculation method, Mach number distribution of the supersonic speed of the tandem spray pipe and the hypersonic speed wind tunnel without adding the steady flow treatment of the porous material is respectively shown in the figures 2 and 3 when the experimental Mach number is 3, the strong shock waves and large separation vortexes in the supersonic speed of the tandem spray pipe and the hypersonic speed wind tunnel can be effectively weakened by reasonably arranging the porous material in the stabilizing section, and the steady flow effect on the supersonic speed of the tandem spray pipe and the hypersonic speed wind tunnel after the porous damping material is added is further verified, so that the effect of improving free incoming flow of the test section is achieved.
The numerical tests show that the porous medium is very important for reducing the disturbance of the incoming flow of the wind tunnel. Meanwhile, the porous medium wall surface has a simple structure and is easy to implement, so that good reference can be provided for engineering application.
The porous medium flow stabilizing method provided by the invention can obviously improve the experimental incoming flow quality of the tandem nozzle supersonic velocity and hypersonic velocity wind tunnel. On the premise of ensuring the normal operation of the unresponsive wind tunnel, the working hours are saved, the period is shortened, the efficiency is improved, and the higher free incoming flow quality of the wind tunnel is ensured.
The invention provides a supersonic velocity and hypersonic velocity wind tunnel flow stabilizing method of a tandem type spray pipe based on porous material flow control, which adopts an active flow control means to reduce or eliminate strong shock wave effect and large flow separation in a stabilizing section of a supersonic velocity and hypersonic velocity tandem type wind tunnel, and greatly improves the free incoming flow quality of the wind tunnel.
It should be noted that, according to the implementation requirement, each step/component described in the present application can be divided into more steps/components, and two or more steps/components or partial operations of the steps/components can be combined into new steps/components to achieve the purpose of the present invention.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A flow stabilizing method for tandem supersonic and hypersonic wind tunnels is characterized by comprising the following steps:
placing a porous material in a stabilizing section, wherein the pore thickness of the porous material disposed upstream of the stabilizing section is greater than the pore thickness of the porous material subsequently disposed.
2. The method of claim 1, wherein the porous material is arranged vertically along the axis of the stabilizing section and the diameter of the porous material is coincident with the diameter of the stabilizing section.
3. The method according to claim 1 or 2, wherein the pore size of the porous material is 0.05mm to 2 mm.
4. The method of claim 3, wherein the porous material has a porosity of 70% to 96%.
5. The method of claim 4, wherein the porous material has a permeability of 1 x 10-9m2～1×10-5m2。
6. A tandem supersonic and hypersonic wind tunnel comprising: a first lance, a stabilizing section, a second lance and a test section, characterized in that a porous material is placed in the stabilizing section, wherein the pore thickness of the porous material arranged upstream of the stabilizing section is larger than the pore thickness of the porous material arranged subsequently.
7. The tandem supersonic and hypersonic wind tunnel of claim 6, wherein said porous material is arranged vertically along an axis of said stabilizing section and has a diameter that is consistent with a diameter of said stabilizing section.
8. The tandem supersonic and hypersonic wind tunnel according to claim 6 or 7, wherein the pore diameter of said porous material is 0.05 mm-2 mm.
9. The tandem supersonic and hypersonic wind tunnel of claim 8, wherein said porous material has a porosity of 70% to 96%.
10. The tandem supersonic and hypersonic wind tunnel of claim 9, wherein said porous material has a permeability of 1 x 10-9m2～1×10-5m2。
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098033A (en) * | 2020-08-04 | 2020-12-18 | 空气动力学国家重点实验室 | A central hypersonic wind tunnel diffuser |
| CN112523896A (en) * | 2020-11-20 | 2021-03-19 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN114813096A (en) * | 2022-06-29 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-layer sintering net test model selection method for hypersonic wind tunnel |
| CN117405351A (en) * | 2023-12-14 | 2024-01-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098033A (en) * | 2020-08-04 | 2020-12-18 | 空气动力学国家重点实验室 | A central hypersonic wind tunnel diffuser |
| CN112523896A (en) * | 2020-11-20 | 2021-03-19 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN112523896B (en) * | 2020-11-20 | 2022-03-04 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN114813096A (en) * | 2022-06-29 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-layer sintering net test model selection method for hypersonic wind tunnel |
| CN117405351A (en) * | 2023-12-14 | 2024-01-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
| CN117405351B (en) * | 2023-12-14 | 2024-03-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
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Application publication date: 20200414 |