CN102426090A - Shock tunnel - Google Patents
Shock tunnel Download PDFInfo
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- CN102426090A CN102426090A CN2011102476184A CN201110247618A CN102426090A CN 102426090 A CN102426090 A CN 102426090A CN 2011102476184 A CN2011102476184 A CN 2011102476184A CN 201110247618 A CN201110247618 A CN 201110247618A CN 102426090 A CN102426090 A CN 102426090A
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Abstract
The invention discloses a shock tunnel which comprises a driving section and a driven section, wherein the diameter of a channel in the driven section is larger than that of a channel in the driving section; a transition section is arranged between the driving section and the driven section; the diameter of a channel in the transition section is gradually enlarged from the driving section to the driven section; the diameter of a channel which is arranged in the transition section and is connected with one end of the driving section is the same as that of the channel in the driving section; and the diameter of a channel which is arranged in the transition section and is connected with one end of the driven section is the same as that of the channel in the driven section. The transition section is adopted to connect the driving section with smaller internal diameter and the driven section with larger internal diameter, and a streamlined gradient curved surface is adopted as the shape of the channel in the transition section, so that boundary layer separation, large separation and the formation of instable vortex can be avoided; therefore, the uniform stability of flow can be improved, the flow loss is less, and the flow quality is improved.
Description
Technical field
The present invention relates to a technology of air suction type high-speed aircraft experimental study, particularly be used for the shock tunnel of hypersonic aircraft ground-based simulation equipment.
Background technology
In the hypersonic aircraft development process, need a large amount of ground simulation experiments, to obtain aircraft aerodynamic force and propulsive performance data.The impulse type shock tunnel is one of a kind of testing equipment that hypersonic flow simulating is provided.Modal shock tunnel is through-type shock tunnel, and promptly shock tunnel drives the section inside dimension with identical by driving section inside dimension; Sometimes in order to improve the wind-tunnel driving force, reach higher stagnation temperature and stagnation pressure, also adopt the shock tunnel of shrinkage type, promptly shock tunnel drives the section inside dimension greater than being driven the section inside dimension; Also having a kind of is the expanding shock tunnel, and shock tunnel drives the section inside dimension less than being driven the section inside dimension, and this wind-tunnel can reduce the driving force of shock tunnel.Because the expanding shock tunnel can produce the influence that special secondaries phenomenon and the mobile quality section of being activated and quilt drive transition section between the section, this wind-tunnel is of little use.
Under some special situation, the expanding shock tunnel has special benefit.As in the detonation driven shock tunnel; Because detonation driven is very capable, can produce very high simulation flow stagnation temperature and stagnation pressure, but when this wind-tunnel carries out hypersonic flow simulating simultaneously; Be difficult to satisfy the tailored contact surface operation condition, the test period of wind-tunnel is shorter.If but the shock tunnel structure through expanding then can reduce the wind-tunnel driving force to a certain extent, thereby satisfy the tailored contact surface operation condition, increased the wind tunnel test time widely.
Summary of the invention
The object of the present invention is to provide a kind of shock tunnel, can weaken secondaries and boundary-layer and disturb the separation flow phenomenon that possibly form, thereby improve the flow quality that the shock tunnel simulation is flowed.
A kind of shock tunnel provided by the invention comprises: drive section and driven section, the said section internal channel diameter that is driven section is greater than the said section internal channel diameter that drives section; Be provided with transition section in said driving section with between by the driving section; The section internal channel diameter of said transition section becomes big gradually by said driving section to the said section that driven; Said transition section identical with the said section internal channel diameter that drives section with the said section internal channel diameter that drives the end that section joins, said transition section identical with the said section internal channel diameter that is driven section with the said section internal channel diameter that is driven the end that section joins.
Preferably, the section internal channel of said transition section is streamlined curved surface.
Preferably, arbitrarily the tangent line in axial direction of any and the angle between the axis are less than or equal to 30 degree on the face of said streamlined curved surface.
Preferably, the section internal channel of said transition section is connected with the said section internal channel smooth transition that drives section.
Preferably, the section internal channel of said transition section is connected with the said section internal channel smooth transition that is driven section.
The present invention adopts little driving section of changeover portion linkage section interior diameter and the big section of being driven of section interior diameter; And adopt the section internal passage shape of fairshaped gradual change curved surface as changeover portion; Avoided boundary-layer to separate and separated greatly and the formation of unstable whirlpool; Thereby improved the uniform and stable property that flows; Flow losses are also less, improved mobile quality.
Description of drawings
Below based on the non-limiting example in the figs the present invention is done further elaboration.
Fig. 1 is an expanding shock tunnel transition section design diagram of the present invention;
Fig. 2 a is the section internal channel of transition section when adopting the structure of expansion suddenly, produces the synoptic diagram that separates the whirlpool; Fig. 2 b is the section internal channel of transition section when adopting the excessive structure of the angle of flare, produces the synoptic diagram that separates the whirlpool; Fig. 2 c is the section internal channel of transition section when adopting the structure of streamlined gradual change, can not produce the synoptic diagram that separates the whirlpool.
Embodiment
As shown in Figure 1, shock tunnel of the present invention comprises: driving section 1 and quilt drive section 4, and the section internal channel diameter of the quilt section of driving 4 is greater than the section internal channel diameter of driving section 1.Be provided with transition section 3 in driving section 1 with between by driving section 4; The section internal channel diameter of transition section 3 is become big by driving section 1 to driving section 4 gradually; The section internal channel diameter with driving the end that section 1 joins of transition section 3 is identical with the section internal channel diameter that drives section 1, and section internal channel diameter transition section 3 and that driven the end that section 4 joins is identical with the section internal channel diameter that is driven section 4.Between transition section 3 and driving section 1, also be provided with diaphragm 2.
In embodiments of the present invention; The section internal channel of transition section 3 is streamlined curved surface; Streamlined curved surface satisfies following condition: arbitrarily the tangent line in axial direction of any and the angle between the axis are less than or equal to 30 degree on the face of streamlined curved surface; The section internal channel of transition section 3 is connected with the section internal channel smooth transition that drives section 1, and the section internal channel of transition section 3 is connected with the section internal channel smooth transition that is driven section 4.
The present invention adopts little driving section of transition section 3 linkage section interior diameters 1 and the big quilt of section interior diameter to drive section 4; And adopt the section internal passage shape of fairshaped gradual change curved surface as transition section 3; Avoided the boundary-layer separation, separated and the formation of unstable whirlpool greatly, thereby improved the uniform and stable property that flows, flow losses are also less; Improved mobile quality, shown in Fig. 2 c.Corresponding with it; Shown in Fig. 2 a and Fig. 2 b; If the section internal channel of transition section 3 adopt the mode of expansion suddenly or expansion angle excessive (be on the face of streamlined curved surface arbitrarily between the tangent line in axial direction of any and the axis greater than 30 degree) time, all can produce and separate the whirlpool.
Claims (5)
1. a shock tunnel comprises: drive section and, it is characterized in that the said section internal channel diameter that is driven the section internal channel diameter of section greater than said driving section by the driving section; Be provided with transition section in said driving section with between by the driving section; The section internal channel diameter of said transition section becomes big gradually by said driving section to the said section that driven; Said transition section identical with the said section internal channel diameter that drives section with the said section internal channel diameter that drives the end that section joins, said transition section identical with the said section internal channel diameter that is driven section with the said section internal channel diameter that is driven the end that section joins.
2. shock tunnel as claimed in claim 1 is characterized in that, the section internal channel of said transition section is streamlined curved surface.
3. shock tunnel as claimed in claim 2 is characterized in that, arbitrarily the tangent line in axial direction of any and the angle between the axis are less than or equal to 30 degree on the face of said streamlined curved surface.
4. like the arbitrary described shock tunnel of claim 1 to 3, it is characterized in that the section internal channel of said transition section is connected with the said section internal channel smooth transition that drives section.
5. like the arbitrary described shock tunnel of claim 1 to 3, it is characterized in that the section internal channel of said transition section is connected with the said section internal channel smooth transition that is driven section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102476184A CN102426090A (en) | 2011-08-24 | 2011-08-24 | Shock tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102476184A CN102426090A (en) | 2011-08-24 | 2011-08-24 | Shock tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102426090A true CN102426090A (en) | 2012-04-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011102476184A Pending CN102426090A (en) | 2011-08-24 | 2011-08-24 | Shock tunnel |
Country Status (1)
| Country | Link |
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| CN (1) | CN102426090A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108168832A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of throat structure for improving tube wind tunnel experiment Reynolds number |
| CN111272377A (en) * | 2020-02-27 | 2020-06-12 | 北京航空航天大学 | Large-scale double-circulation back-cooling type low-temperature environment wind tunnel |
| CN113702432A (en) * | 2021-08-30 | 2021-11-26 | 中国科学院力学研究所 | Test device for refrigerating by utilizing gas pressure energy and control method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3618380A (en) * | 1968-11-05 | 1971-11-09 | Gen Electric | Continuous discharge driver freepiston shock tunnel |
| DE4224488A1 (en) * | 1992-07-24 | 1994-01-27 | Audi Ag | Wind tunnel, esp. for aero-acoustic measurements - has nozzle, measurement section, air collection hopper, constriction and diffuser in series in flow direction |
| JPH06201512A (en) * | 1992-12-28 | 1994-07-19 | Ebara Corp | Air flow outlet |
| CN2742202Y (en) * | 2003-12-26 | 2005-11-23 | 陶峰 | Novel spreading bent pipe |
| CN2802097Y (en) * | 2005-06-24 | 2006-08-02 | 天津市环科机动车尾气催化净化技术有限公司 | Arc expansion-contraction pipe catalytic converter |
| CN101135323A (en) * | 2007-09-30 | 2008-03-05 | 湖南科技大学 | Energy-saving type mine main ventilator diffuser |
| CN102023079A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic free vortex mixing layer wind tunnel |
| CN102023077A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic velocity axisymmetrical boundary layer wind tunnel |
-
2011
- 2011-08-24 CN CN2011102476184A patent/CN102426090A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3618380A (en) * | 1968-11-05 | 1971-11-09 | Gen Electric | Continuous discharge driver freepiston shock tunnel |
| DE4224488A1 (en) * | 1992-07-24 | 1994-01-27 | Audi Ag | Wind tunnel, esp. for aero-acoustic measurements - has nozzle, measurement section, air collection hopper, constriction and diffuser in series in flow direction |
| JPH06201512A (en) * | 1992-12-28 | 1994-07-19 | Ebara Corp | Air flow outlet |
| CN2742202Y (en) * | 2003-12-26 | 2005-11-23 | 陶峰 | Novel spreading bent pipe |
| CN2802097Y (en) * | 2005-06-24 | 2006-08-02 | 天津市环科机动车尾气催化净化技术有限公司 | Arc expansion-contraction pipe catalytic converter |
| CN101135323A (en) * | 2007-09-30 | 2008-03-05 | 湖南科技大学 | Energy-saving type mine main ventilator diffuser |
| CN102023079A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic free vortex mixing layer wind tunnel |
| CN102023077A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic velocity axisymmetrical boundary layer wind tunnel |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108168832A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of throat structure for improving tube wind tunnel experiment Reynolds number |
| CN108168832B (en) * | 2016-12-08 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of throat structure improving tube wind tunnel test Reynolds number |
| CN111272377A (en) * | 2020-02-27 | 2020-06-12 | 北京航空航天大学 | Large-scale double-circulation back-cooling type low-temperature environment wind tunnel |
| CN113702432A (en) * | 2021-08-30 | 2021-11-26 | 中国科学院力学研究所 | Test device for refrigerating by utilizing gas pressure energy and control method |
| CN113702432B (en) * | 2021-08-30 | 2022-05-17 | 中国科学院力学研究所 | Test device for refrigerating by utilizing gas pressure energy and control method |
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Application publication date: 20120425 |