CN203688195U - Supersonic velocity diffusion device with active injection - Google Patents
Supersonic velocity diffusion device with active injection Download PDFInfo
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- CN203688195U CN203688195U CN201320845013.XU CN201320845013U CN203688195U CN 203688195 U CN203688195 U CN 203688195U CN 201320845013 U CN201320845013 U CN 201320845013U CN 203688195 U CN203688195 U CN 203688195U
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Abstract
The utility model discloses a supersonic velocity diffusion device with active injection, belonging to the aerodynamic field, and comprises a diffuser front segment with a first taper cylinder and a first straight pipe, wherein the bottom opening of the first taper cylinder is opposite with a nozzle of a jet pipe ejecting supersonic velocity air-flow in a mode of being spaced at a certain distance, one end of the first straight pipe is in communication with an upper opening, and the sidewall of the other end is provided with a boss; an injector with a housing, wherein the housing comprises a straight barrel and a second taper cylinder, the bottom of the straight barrel is provided with a first through hole, the sidewall of the straight barrel is provided with a second through hole communicating with an injection air source pipeline, the connecting part between the straight barrel and the second taper cylinder is a concave platform bending to the axis direction of the straight barrel, the other end of the first straight pipe penetrates through the first through hole to extend into the straight barrel, and the boss and the concave platform are opposite in the direction perpendicular to the axis direction of the straight barrel; and a diffuser rear segment with a third taper cylinder. According to the technical scheme of the utility model, wind tunnels can realize a stable flow field under the condition of high Mach number to meet model test demands.
Description
Technical field
The utility model belongs to aerodynamics field, particularly a kind of supersonic speed diffuser arrangement with active injection.
Background technology
Mach number is more than or equal in 8 conventional hypersonic wind tunnel, gases at high pressure (supersonic flow) accelerate ejection by jet pipe, it in test section, is free jet, meeting under certain pressure ratio condition, requiring provides for model test the uniform flow field meeting the demands, actual conditions are that the pressure of wind tunnel nozzle main flow is generally restricted, and can only reach certain value; When main flow pressure is difficult to improve again, along with the Mach number of wind tunnel operation is higher, the static pressure of nozzle exit is lower, requires exhaust system that enough low back pressure is provided, and could meet wind tunnel operation.
At present, conventional hypersonic wind tunnel has two kinds of alternative low back pressure producing methods.The first, pressure-vacuum method of operation, it uses large volume vacuum sphere, in advance vacuum sphere is pumped into low pressure, and pressure can arrive below 100Pa.The second, pressure-injection method of operation, it uses injector, by the expansion of pressure gas, produces the environment under low pressure needing in pipeline, and injector uses according to the requirement series connection of pressure ratio, can be divided into 1 grade, and 2 grades, 3 grades etc.With the increase of injector progression, can obtain more and more lower back pressure.
Surpass-super the injector of National University of Defense technology's research, build altitude simulation platform, carry out the performance test of altitude engine, mainly to produce once stream with high-temperature high-pressure fuel gas, carry out the Secondary Flow that injection engine jet pipe produces, analyze the feature of super-super injection, provide and realize super-super feasibility of mixing injection, but do not study the anterior problem that forms uniform flow field of injector, only be given under super-super injection condition and there is pressurization by injection, can realize air-discharging and supercharging, reach the function of altitude simulation.
At present, Mach number is more than or equal to 5 conventional hypersonic wind tunnel, and nozzle exit forms uniform FLOW FIELD IN FREE JETS, and exhaust system adopts air ejector, the FL-31 hypersonic wind tunnel of for example CARDC, the FD-07 hypersonic wind tunnel of CAAA.Wherein ultra-expanded section device is all the contraction-like barrel shaped structure of hydraucone, belongs to the passive type diffusion of gas free jet.In the certain situation of rear portion injector suction capactity, with Mach number, Ma is higher, is generally Ma >=8, and negative margin appears in flow field, and region diminishes; Wind-tunnel completes model test, is difficult to, and even can not set up qualified flow field.
Summary of the invention
In order to solve the problem of prior art, the utility model embodiment provides a kind of supersonic speed diffuser arrangement with active injection, it comprises: the diffuser leading portion with the first cone cylinder and the first straight tube, the bottom opening of described the first cone cylinder is relative with the spout of the jet pipe of ejection supersonic flow in the mode keeping at a certain distance away, the diameter of described bottom opening is greater than the diameter of the upper shed of described the first cone cylinder, one end of described the first straight tube is communicated with described upper shed, on the sidewall of the other end, is provided with boss, there is the injector of housing, described housing comprises straight bucket and the second cone cylinder, the bottom of described straight bucket has the first through hole, the sidewall of described straight bucket has the second through hole that is communicated with injection gas source pipe, the bung of described straight bucket is communicated with the bottom opening of described the second cone cylinder, the diameter of the bottom opening of described the second cone cylinder is greater than the diameter of the upper shed of described the second cone cylinder, described straight bucket is the concave station to the axis direction bending of described straight bucket with the junction of described the second cone cylinder, the other end of described the first straight tube is through described the first through hole, extend in described straight bucket, the boss of telling and described concave station relative on the axis direction of vertical described straight bucket, and there is the diffuser back segment of third hand tap cylinder, and the upper shed of the bottom opening of described third hand tap cylinder and described the second cone cylinder is communicated with, and the diameter of described bottom opening is less than the diameter of the upper shed of described third hand tap cylinder.
In supersonic speed diffuser arrangement as above, preferably, described jet pipe is the jet pipe of hypersonic wind tunnel, the upper shed of described the second cone cylinder and the bottom opening of described third hand tap cylinder are all fixed on the test section rear wall of described hypersonic wind tunnel, and the upper shed of described third hand tap cylinder is communicated with the pipeline of the exhaust system of described hypersonic wind tunnel.
In supersonic speed diffuser arrangement as above, preferably, described concave station is circular arc, and described boss is triangular in shape.
In supersonic speed diffuser arrangement as above, preferably, the minimum point of the described concave station that is circular arc on the axis direction of vertical described straight bucket is relative with the peak of described boss triangular in shape.
In supersonic speed diffuser arrangement as above, preferably, the angle of flare of described third hand tap cylinder is less than or equal to 8 °.
In supersonic speed diffuser arrangement as above, preferably, described the first straight tube is connected by flange with described straight bucket, and described the second cone cylinder is connected by flange with described third hand tap cylinder.
In supersonic speed diffuser arrangement as above, preferably, the flange connections of described the first straight tube and described straight bucket is filled with red copper pad, and described the second cone cylinder is filled with red copper pad with the flange connections of described third hand tap cylinder.
In supersonic speed diffuser arrangement as above, preferably, the axis of the axis of described spout, the axis of described diffuser leading portion, described housing and the axis coaxle of described diffuser back segment.
In supersonic speed diffuser arrangement as above, preferably, described injector is annular ejector.
In supersonic speed diffuser arrangement as above, preferably, described diffuser back segment also comprises the second straight tube being communicated with the upper shed of described third hand tap cylinder.
The beneficial effect that the utility model embodiment brings is as follows:
By adopting initiatively injection to carry out supercharging to the supersonic flow of conventional hypersonic wind tunnel jet pipe in supersonic speed diffuser arrangement, meet the pressure ratio condition of wind tunnel operation needs, improve the performance of nozzle flow field, and then realize wind tunnel operation in High Mach number situation, stablizing of flow field, has met model test demand.
Brief description of the drawings
Fig. 1 is the actual figure of use structure of a kind of supersonic speed diffuser arrangement of providing of the utility model embodiment;
Fig. 2 is the actual figure of structure of a kind of supersonic speed diffuser arrangement of providing of the utility model embodiment;
Fig. 3 is the actual figure of structure of a kind of diffuser leading portion of providing of the utility model embodiment;
Fig. 4 is the actual figure of structure of a kind of injector of providing of the utility model embodiment;
Fig. 5 is the actual figure of a kind of diffuser rear section structure that the utility model embodiment provides;
Fig. 6 is the actual figure of structure of a kind of injection gas source pipe of providing of the utility model embodiment;
Wherein, in figure, symbol description is as follows:
The jet pipe of 1 conventional hypersonic wind tunnel,
2 diffuser leading portions, 21 first cone cylinders, 22 first straight tubes, 23 boss, 24 ring flanges,
3 housings, 31 second cone cylinders, 32 straight buckets, 33 concave stations, 34 ring flanges,
4 test section rear walls,
5 diffuser back segments, 51 third hand tap cylinders, 52 second straight tubes, 53,54 ring flanges,
61 injection gas source pipes, 62 ring flanges.
Embodiment
For making the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with accompanying drawing, the utility model embodiment is described in further detail.
Referring to Fig. 1-Fig. 6, the utility model embodiment provides a kind of supersonic speed diffuser arrangement with active injection, and it comprises: diffuser leading portion 2, injector and diffuser back segment 5.Diffuser leading portion is used for collecting supersonic flow, in practice, supersonic flow can be the primary air of the jet pipe ejection of conventional hypersonic wind tunnel, can also for need diffusion by injection incoming flow, the present embodiment does not limit this, described as example by jet pipe 1 ejection of conventional hypersonic wind tunnel taking supersonic flow in the present embodiment, now, this supersonic speed diffuser arrangement is the Supersonic diffuser+ of conventional hypersonic wind tunnel test section outlet.Injector expands for the acceleration of injection supersonic flow, and makes supersonic flow go out interruption-forming low pressure supersonic jet at injector.Diffuser back segment is used to form the second throat of supersonic speed diffuser arrangement, and by shock wave deceleration supercharging, supersonic flow gradually becomes subsonic speed air-flow therein, and can enter the exhaust system of hypersonic wind tunnel, can also enter the inlet duct of injector.
Particularly, referring to Fig. 3, the first straight tube 22 that diffuser leading portion comprises the first cone cylinder 21 and is welded to connect with the first cone cylinder 21.The bottom opening (being the left opening of the first cone cylinder in Fig. 1) of the first cone cylinder 21 is relative with the spout of jet pipe 1, to collect the supersonic flow from jet pipe 1, between this bottom opening and jet pipe 1 gapped (keeping at a certain distance away); The diameter of the upper shed (being the right opening of the first cone cylinder in Fig. 1) of the first cone cylinder 21 is less than the diameter of this bottom opening, this upper shed is communicated with one end of the first straight tube 22, on the sidewall of the other end of the first straight tube 22, be provided with the boss 23 that forms injector venturi, the both sides of boss 23 are respectively subsonic speed contraction section wall (being left wall in Fig. 1) and the supersonic speed expansion segment wall (being right wall in Fig. 1) of the jet pipe of injector.The first cone cylinder 21 is bell mouth shape.In wind-tunnel uses, in order to reach higher extension pressur efficiency, need determine according to the Mach number of supersonic wind tunnel jet pipe the distance of the spout of first bottom opening of cone cylinder 21 and the jet pipe of supersonic wind tunnel, for example, be 195mm for spout (outlet) diameter, the jet pipe of Mach 2 ship 8, this distance is 300mm, because the diameter of this bottom opening is also relevant to the Mach number of supersonic wind tunnel jet pipe, in these cases, the diameter of this bottom opening is 205mm.That is to say the jet pipe 1 according to different Mach number, need the diffuser leading portion in supporting different length with interval and aperture.
Referring to Fig. 4, injector comprises the housing 3 for pressure-bearing, and it is thick-walled structure, and comprises straight bucket 32 and the second cone cylinder 31.Have in the bottom of straight bucket 32 (being the left side of straight bucket 32) the first through hole coordinating with the first straight tube 22 in Fig. 1; Have and be communicated with injection gas source pipe 61(referring to Fig. 6 at the sidewall of straight bucket 32) the second through hole, injection gas source pipe 61 is connected with this side by the ring flange 62 on it; The bung of straight bucket 32 is communicated with the bottom opening (being the left opening of the second cone cylinder 31 in Fig. 1) of the second cone cylinder 31.The diameter of the bottom opening of the second cone cylinder 31 is greater than the diameter of the upper shed (being the right opening of the second cone cylinder 31 in Fig. 1) of the second cone cylinder 31, now, and the cone cylinder of the second cone cylinder 31 for shrinking.Junction at straight bucket 32 and the second cone cylinder 31 is the concave station 33 to the axis direction bending of straight bucket 32.In the time of application, the other end of the first straight tube 12, through the first through hole, extend in straight bucket 32, until boss 23 is relative on the axis direction of straight vertical bucket with concave station 33, thereby makes this concave station 33 and boss 23 form injector venturi (venturi of injector jet pipe).Preferably, concave station 33 is circular arc, that is to say, the concave station that the junction of straight bucket 32 and the second cone cylinder 31 is arc transition, and boss 23 is triangular in shape.More preferably, the minimum point of the concave station 33 that is circular arc on the axis direction of straight vertical bucket is relative with the peak (summit) of boss 23 triangular in shape.Because housing 3 and injection gas source pipe 61 need bear higher pressure, for example 4.0MPa, therefore its material is all selected withstand voltage material.Injector is preferably annular ejector.At the jet pipe of different diffuser leading portion different annular ejectors capable of being combined, thereby change injection area, meet test demand.For example, be 195mm for spout (outlet) diameter of wind tunnel nozzle, the jet pipe of Mach 2 ship 8, distance between bottom opening and the spout of the first cone cylinder is 300mm, the diameter of this bottom opening is 205mm, the jet pipe Mach 2 ship 4 of annular ejector, injection area 0.35.
Referring to Fig. 5, diffuser back segment comprises that the bottom opening (being left opening in Fig. 1) of third hand tap cylinder 51, the third hand tap cylinders 51 is communicated with the upper shed of the second cone cylinder 31, and the diameter of this bottom opening is less than the diameter of the upper shed (being right opening in Fig. 1) of third hand tap cylinder 51.Further, diffuser back segment also comprises the second straight tube 52, and now the second straight tube 52 is communicated with the exhaust system of hypersonic wind tunnel by the ring flange 54 on it, can also be communicated with the inlet duct of injector.In practice, the internal diameter of the second straight tube 52 can be 250mm.
For preventing burbling, the angle of flare (angle between barrel and the axis of third hand tap cylinder) of third hand tap cylinder 51 is not more than 8 °, is preferably 6 °.
For simple in structure being convenient to connected, on the sidewall of the first straight tube 22, be provided with ring flange 24, this ring flange 24 is fixed with the bottom of straight bucket; On the sidewall of the close upper shed of the second cone cylinder 31, be provided with ring flange 34, on the sidewall of the close bottom opening of third hand tap cylinder 51, be provided with ring flange 53, ring flange 34 is connected with ring flange 53.When mounted, the test section rear wall 4 of supersonic wind tunnel provides support for this supersonic speed diffuser arrangement, and particularly, the second cone cylinder 31 is fixed on the rear wall of test section by ring flange 53 by ring flange 34, the third hand tap cylinders 51.Be filled with red copper pad at above-mentioned flange connections, to ensure the sealing of junction.
The axis of the spout of the jet pipe 1 of supersonic wind tunnel, the axis of diffuser leading portion, the axis of housing and the axis coaxle of diffuser back segment are so that the passage of central gas stream (air-flow in supersonic speed diffuser arrangement) meets coaxial requirement.Further, the internal face smooth transition of the inner circle of test section wall and housing, diffuser back segment, without reverse step.
The principle of the supersonic speed diffuser arrangement below the utility model embodiment being provided describes.
Conventional hypersonic wind tunnel nozzle exit air-flow is supersonic flow, for meeting testing requirements, need to have one section of free jet length, because it is unlike injector jet pipe, has very high energy to expand to produce high velocity, low pressure and flow in shorter distance.Wind tunnel nozzle jet boundary static pressure is very low, is generally border by compression.Under such low pressure condition, use diffuser leading portion to carry out air-flow diffusion, be mainly to play the effect of collecting air-flow.The static pressure of experimental flow field downstream free jet is very low, and afterbody jet becomes oblique shock wave and slows down, and quilt around high pressurized air compresses, and becomes gradually subsonic speed air-flow, flow further downstream.Adopt initiatively injection at the injector between diffuser leading portion and diffuser back segment, according to waiting hydrostatic pressure condition, the main jet pipe jet shrinking in diffuser leading portion changes contraction state, becomes forward jet, enter injector mixing chamber (the second cone cylinder place), realize super-super injection.The inwall of the outer wall of diffuser leading portion and the housing of injector, form pressure-bearing and stay chamber (space between straight bucket and the first straight tube) and supersonic speed nozzle ring (concave station and boss place), supersonic jet is in outlet downstream (the housing rear portion of the injector) deflection of expanding, form pneumatic venturi at the end of injector housing, complete the pressurization to primary air, form mixed supersonic jet, enter diffuser back segment deceleration supercharging.That is to say that this supersonic speed diffuser arrangement is under pressure-injector state, by the active injection in it, the hypersonic jet that comes from jet pipe is realized to function of increasing pressure.
In sum, the utility model embodiment by adopting initiatively injection to carry out supercharging to the supersonic flow of conventional hypersonic wind tunnel jet pipe in supersonic speed diffuser arrangement, meet the pressure ratio condition of wind tunnel operation needs, improve the performance of nozzle flow field, and then realize wind tunnel operation in High Mach number situation, stablizing of flow field, has met model test demand, has improved Flow Field in Wind Tunnel quality.
These are only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any amendment of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (10)
1. the supersonic speed diffuser arrangement with active injection, is characterized in that, described supersonic speed diffuser arrangement comprises:
There is the diffuser leading portion of the first cone cylinder and the first straight tube, the bottom opening of described the first cone cylinder is relative with the spout of the jet pipe of ejection supersonic flow in the mode keeping at a certain distance away, the diameter of described bottom opening is greater than the diameter of the upper shed of described the first cone cylinder, one end of described the first straight tube is communicated with described upper shed, on the sidewall of the other end, is provided with boss;
There is the injector of housing, described housing comprises straight bucket and the second cone cylinder, the bottom of described straight bucket has the first through hole, the sidewall of described straight bucket has the second through hole that is communicated with injection gas source pipe, the bung of described straight bucket is communicated with the bottom opening of described the second cone cylinder, the diameter of the bottom opening of described the second cone cylinder is greater than the diameter of the upper shed of described the second cone cylinder, described straight bucket is the concave station to the axis direction bending of described straight bucket with the junction of described the second cone cylinder, the other end of described the first straight tube is through described the first through hole, extend in described straight bucket, the boss of telling and described concave station relative on the axis direction of vertical described straight bucket, and
Have the diffuser back segment of third hand tap cylinder, the bottom opening of described third hand tap cylinder is communicated with the upper shed of described the second cone cylinder, and the diameter of described bottom opening is less than the diameter of the upper shed of described third hand tap cylinder.
2. supersonic speed diffuser arrangement according to claim 1, it is characterized in that, described jet pipe is the jet pipe of hypersonic wind tunnel, the upper shed of described the second cone cylinder and the bottom opening of described third hand tap cylinder are all fixed on the test section rear wall of described hypersonic wind tunnel, and the upper shed of described third hand tap cylinder is communicated with the pipeline of the exhaust system of described hypersonic wind tunnel.
3. supersonic speed diffuser arrangement according to claim 1, is characterized in that, described concave station is circular arc, and described boss is triangular in shape.
4. supersonic speed diffuser arrangement according to claim 3, is characterized in that, the minimum point of the described concave station that is circular arc on the axis direction of vertical described straight bucket is relative with the peak of described boss triangular in shape.
5. supersonic speed diffuser arrangement according to claim 1, is characterized in that, the angle of flare of described third hand tap cylinder is less than or equal to 8 °.
6. supersonic speed diffuser arrangement according to claim 1, is characterized in that, described the first straight tube is connected by flange with described straight bucket, and described the second cone cylinder is connected by flange with described third hand tap cylinder.
7. supersonic speed diffuser arrangement according to claim 6, is characterized in that, the flange connections of described the first straight tube and described straight bucket is filled with red copper pad, and described the second cone cylinder is filled with red copper pad with the flange connections of described third hand tap cylinder.
8. supersonic speed diffuser arrangement according to claim 1, is characterized in that, the axis of the axis of described spout, the axis of described diffuser leading portion, described housing and the axis coaxle of described diffuser back segment.
9. supersonic speed diffuser arrangement according to claim 1, is characterized in that, described injector is annular ejector.
10. supersonic speed diffuser arrangement according to claim 1, is characterized in that, described diffuser back segment also comprises the second straight tube being communicated with the upper shed of described third hand tap cylinder.
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| CN201320845013.XU CN203688195U (en) | 2013-12-19 | 2013-12-19 | Supersonic velocity diffusion device with active injection |
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| CN201320845013.XU CN203688195U (en) | 2013-12-19 | 2013-12-19 | Supersonic velocity diffusion device with active injection |
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| CN104458190A (en) * | 2014-12-09 | 2015-03-25 | 苟仲武 | Liquid air source energy-saving efficient wind tunnel device and method thereof |
| CN104458194A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Hydraulic drive device and mode for axial movement of wind tunnel super expansion segment |
| CN105043711A (en) * | 2015-08-04 | 2015-11-11 | 北京航天长征飞行器研究所 | Wind tunnel diffuser compatible with multiple nozzles and wind tunnel diffusion method |
| CN105443268A (en) * | 2015-11-26 | 2016-03-30 | 南京航空航天大学 | Bypass type passive double-throat pneumatic vector spraying pipe with flow regulating function and control method |
| CN106196038A (en) * | 2016-08-05 | 2016-12-07 | 中国航天空气动力技术研究院 | The auxiliary combustion equipment of coal-fired gasification furnace |
| CN106838902A (en) * | 2016-12-12 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of supersonic speed combustion gas injector |
| CN108416183A (en) * | 2018-06-06 | 2018-08-17 | 中国人民解放军国防科技大学 | Design method of two-dimensional support plate integrated structure for ejector |
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| CN104458194A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Hydraulic drive device and mode for axial movement of wind tunnel super expansion segment |
| CN104458190A (en) * | 2014-12-09 | 2015-03-25 | 苟仲武 | Liquid air source energy-saving efficient wind tunnel device and method thereof |
| CN105043711A (en) * | 2015-08-04 | 2015-11-11 | 北京航天长征飞行器研究所 | Wind tunnel diffuser compatible with multiple nozzles and wind tunnel diffusion method |
| CN105443268B (en) * | 2015-11-26 | 2017-07-18 | 南京航空航天大学 | Passive pair of venturi fluidic vectoring nozzle of bypass type with flow regulating function and control method |
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| CN112443518A (en) * | 2020-11-23 | 2021-03-05 | 中国航天空气动力技术研究院 | Supersonic air ejector |
| CN112945509A (en) * | 2021-04-22 | 2021-06-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Opening plugging device for contraction section of hypersonic speed wind tunnel diffuser |
| CN113369029A (en) * | 2021-04-30 | 2021-09-10 | 中国航天空气动力技术研究院 | Injection type low-pressure over-distance gas acceleration spray head |
| CN113389759A (en) * | 2021-06-21 | 2021-09-14 | 郭孝国 | Injection device |
| CN113758672A (en) * | 2021-08-26 | 2021-12-07 | 中国航天空气动力技术研究院 | High-efficient water-cooling diffuser of electric arc wind-tunnel |
| CN113758672B (en) * | 2021-08-26 | 2024-03-26 | 中国航天空气动力技术研究院 | High-efficient water-cooling diffuser of electric arc wind tunnel |
| CN113701984A (en) * | 2021-10-28 | 2021-11-26 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel diffuser and design method thereof |
| CN113701984B (en) * | 2021-10-28 | 2022-01-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel diffuser and design method thereof |
| RU2770320C1 (en) * | 2021-11-09 | 2022-04-15 | Акционерное общество "Центральный научно-исследовательский институт машиностроения" (АО "ЦНИИмаш") | Gas-dynamic pressure chamber |
| CN114279671A (en) * | 2022-03-03 | 2022-04-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel |
| CN114279671B (en) * | 2022-03-03 | 2022-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel |
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