CN204279967U - A kind of aircraft adopting Submerged Inlet - Google Patents
A kind of aircraft adopting Submerged Inlet Download PDFInfo
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- CN204279967U CN204279967U CN201420716928.5U CN201420716928U CN204279967U CN 204279967 U CN204279967 U CN 204279967U CN 201420716928 U CN201420716928 U CN 201420716928U CN 204279967 U CN204279967 U CN 204279967U
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- vortex generator
- submerged inlet
- inlet
- submerged
- thin slice
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Abstract
The utility model discloses a kind of aircraft adopting Submerged Inlet, comprise body, body arranges Submerged Inlet, at least one pair of vortex generator is set in body surface Submerged Inlet import upstream position body plane of symmetry bilateral symmetry.Vortex generator is provided with in missile airframe skin-surface inlet channel upstream, whirlpool is created at boundary layer region, strengthen the blending of boundary 1ayer low energy stream and main flow, effectively inhibit the separation of boundary layer airflow, significantly improve the total pressure recovery coefficient of inlet channel under low discharge state.
Description
Technical field
The utility model relates to a kind of aircraft, particularly relates to a kind of aircraft adopting Submerged Inlet.
Background technology
Submerged Inlet not only effectively can reduce frontal resistance and the radar scattering area of aircraft because wind area is little, and the fusion of itself and body makes the size of body reduce, and is conducive to installing, transport and multi-platform transmitting.Therefore, Submerged Inlet is being subject to paying close attention to more and more widely and applying.
But the import of Submerged Inlet is placed in the low energy stream of body boundary-layer completely, can not utilize incoming flow punching press as S shape inlet channel, before only relying on, the pressure gradient at lip place and incline place entrainments whirlpool air inlet.Especially, when Submerged Inlet is operated in low discharge state, entrainment vortices breakdown too little, the air inlet weak effect of Submerged Inlet.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Utility model content
For the problem that current Submerged Inlet total pressure recovery coefficient when low discharge mode of operation is lower, the utility model technical issues that need to address are to provide the aircraft that a kind of total pressure recovery coefficient is higher and discharge flow distortion is less.
For solving technical matters of the present utility model, the technical solution adopted in the utility model is:
Adopt an aircraft for Submerged Inlet, comprise body, described body arranges Submerged Inlet, at least one pair of vortex generator is set in body surface Submerged Inlet import upstream position body plane of symmetry bilateral symmetry.
Described vortex generator is a kind of section bar of " T " font, and described vortex generator comprises bottom surface thin slice and longitudinal surface thin slice, and described longitudinal surface thin slice is arranged along the median perpendicular of bottom surface thin slice.
The bottom surface of described vortex generator is affixed on body surface, described vortex generator and the described body plane of symmetry in a certain angle, angular range is at 10-45 °.
The beneficial effects of the utility model: be provided with vortex generator in missile airframe skin-surface inlet channel upstream, whirlpool is created at boundary layer region, strengthen the blending of boundary 1ayer low energy stream and main flow, effectively inhibit the separation of boundary layer airflow, significantly improve the total pressure recovery coefficient of inlet channel under low discharge state.
Accompanying drawing explanation
Fig. 1 is front view of the present utility model.
Fig. 2 is lateral plan of the present utility model.
Fig. 3 is the structural representation of vortex generator in the utility model.
Wherein, 1, body, 2, vortex generator, 21, bottom surface thin slice, 22, longitudinal surface thin slice, 3, Submerged Inlet.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.Following examples, only for illustration of the utility model, are not used for limiting protection domain of the present utility model.
With reference to Fig. 1-2, a kind of aircraft adopting Submerged Inlet of the present utility model, comprise body 1, body 1 is arranged Submerged Inlet 3, at least one pair of vortex generator 2 is set in body 1 surperficial Submerged Inlet 3 import upstream position body 1 plane of symmetry bilateral symmetry.
With reference to figure 3, vortex generator 2 is section bars of a kind of " T " font, and vortex generator 2 comprises bottom surface thin slice 21 and longitudinal surface thin slice 22, and longitudinal surface thin slice 22 is arranged along the median perpendicular of bottom surface thin slice 21.
The bottom surface of vortex generator 2 is affixed on body 1 surface, and vortex generator 2 is in a certain angle with body 1 plane of symmetry, and angular range is at 10-45 °.
In missile flight process, vortex generator 3 is placed in the boundary 1ayer of Submerged Inlet 3 import upstream body 1 surface flow field, the whirlpool that vortex generator 3 produces can suppress the separation of boundary layer airflow, improves the serviceability of inlet channel 3 under low discharge state.
Body 1 surperficial Fighter Inlet upstream position body 1 plane of symmetry bilateral symmetry arrange a pair or two couples of vortex generator 3(that is, vortex generator 3 must be installed on the body covering of body 1 plane of symmetry both sides in couples and symmetrically), the height of vortex generator 3 is no more than the boundary layer thickness of locality, installation site, vortex generator 3 is cuboid thin slices, can not significantly improve resistance like this while raising inlet characteristic.
That is, when outer gas stream is before entering inlet channel, when vortex generator 3, produce whirlpool, whirlpool can strengthen the blending of boundary 1ayer low energy stream with main flow, suppresses separation of boundary layer, significantly can improve the air inlet effect of inlet channel under low discharge state.
The Submerged Inlet performance improvement that prior art is disclosed blows based on body surface and the utility model are essentially different in principle based on the Submerged Inlet performance improvement of body surface eddy producer.It is dispelled by the boundary 1ayer low energy stream of high velocity air by body surface that prior art is blown, and makes it can not flow into inside inlet channel, can improve the total pressure recovery coefficient of inlet channel; And the utility model arranges vortex generator, then by producing the blending of entrainmenting whirlpool stiffened edge interlayer and main flow, to prevent the separation of boundary layer airflow, and the air inlet ability effectively improved under intake duct starting stage low discharge state and total pressure recovery coefficient.
The Submerged Inlet based on body surface eddy producer that the utility model proposes, by installing several to vortex generator on Fighter Inlet upstream body surface, the total pressure recovery coefficient of Submerged Inlet low discharge state can be significantly improved like this, there is good engineer applied and be worth.
Claims (3)
1. adopt an aircraft for Submerged Inlet, comprise body, it is characterized in that: described body arranges Submerged Inlet, at least one pair of vortex generator is set in body surface Submerged Inlet import upstream position body plane of symmetry bilateral symmetry.
2. a kind of aircraft adopting Submerged Inlet according to claim 1, it is characterized in that: described vortex generator is a kind of section bar of " T " font, described vortex generator comprises bottom surface thin slice and longitudinal surface thin slice, and described longitudinal surface thin slice is arranged along the median perpendicular of bottom surface thin slice.
3. a kind of aircraft adopting Submerged Inlet according to claim 1, is characterized in that: the bottom surface of described vortex generator is affixed on body surface, described vortex generator and the described body plane of symmetry in a certain angle, angular range is at 10-45 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420716928.5U CN204279967U (en) | 2014-11-26 | 2014-11-26 | A kind of aircraft adopting Submerged Inlet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420716928.5U CN204279967U (en) | 2014-11-26 | 2014-11-26 | A kind of aircraft adopting Submerged Inlet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204279967U true CN204279967U (en) | 2015-04-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420716928.5U Active CN204279967U (en) | 2014-11-26 | 2014-11-26 | A kind of aircraft adopting Submerged Inlet |
Country Status (1)
| Country | Link |
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| CN (1) | CN204279967U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104386255A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Aircraft employing embedded air inlet channel |
| CN117326073A (en) * | 2023-11-09 | 2024-01-02 | 北京北航天宇长鹰无人机科技有限公司 | Buried air inlet channel with stepped boundary layer separation channel and unmanned aerial vehicle |
-
2014
- 2014-11-26 CN CN201420716928.5U patent/CN204279967U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104386255A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Aircraft employing embedded air inlet channel |
| CN117326073A (en) * | 2023-11-09 | 2024-01-02 | 北京北航天宇长鹰无人机科技有限公司 | Buried air inlet channel with stepped boundary layer separation channel and unmanned aerial vehicle |
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