CN105257635A - Suction method for auxiliary boundary layer in supersonic velocity runner - Google Patents
Suction method for auxiliary boundary layer in supersonic velocity runner Download PDFInfo
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Abstract
The invention discloses a suction method for an auxiliary boundary layer in a supersonic velocity runner. A micro vortex generator is arranged in the boundary layer so that upstream incoming flow containing boundary layer fluid can be gradually lifted along the surface of the micro vortex generator during downstream flowing; sweepback edges are arranged on the two sides of the upper surface of the micro vortex generator so that bottom-layer low-speed fluid moving to the boundary layer of the sweepback edges can disengage and a streamwise vortex rich in bottom-layer low-speed fluid can be formed, and the streamwise vortex is driven by the upper-layer high-speed fluid of the boundary layer to move along the side walls of the two sides of the micro vortex generator to the tail of the micro vortex generator; and due to the fact that a fluid suction device is arranged on the tail of the micro vortex generator and used for sucking away the streamwise vortex which is transmitted to the tail of the micro vortex generator and rich in bottom-layer low-speed fluid, large-scale flowing separation caused when the speed and energy of the bottom-layer low-speed fluid of the boundary layer are too low, and meanwhile the upper-layer high-speed fluid of the boundary layer is reserved so that flow loss can be reduced.
Description
Technical field
The present invention relates to flowing control field, especially, relate to assisted border layer suction method in a kind of high-speed aircraft propulsion system internal ultrasonic speed runner.
Background technique
Boundary layer separation is the universal phenomenon existed from common low-speed operations device to ultrasound velocity, hypersonic aircraft aerodynamic surface and motor inner flow passage.The appearance of boundary layer separation causes the sharply deterioration of increasing sharply of flight vehicle aerodynamic resistance and lift efficiency usually, and the UNSTEADY FLOW of large scale is separated fatigue and the destruction that can aggravate housing construction.The large scale boundary layer separation that in ultrasound velocity and hypersonic aircraft inner flow passage, shock and boundary layer interference brings out is the major reason that aircraft inlet characteristic deficiency even cannot start.Thus boundary layer separation suppresses to be current ultrasonic speed, hypersonic flight need solution major issue in designing.Current boundary layer suction is the boundary layer flow control device of main flow in Flight Vehicle Design.Near wall region boundary layer fluid speed outwards increases to mainstream speed by zero gradually from wall, the overall level of momentum extracting its bottom part low speed, low energy fluid to improve boundary layer by flow control technique is expected in engineer applied, and then improve boundary layer anti-reflective pressure energy power, thus reach the effect suppressing or weaken wall and be separated, and meanwhile retain its upper strata highspeed portion as far as possible to reduce flow loss.
But the adverse pressure gradient finding SHOCK WAVE INDUCED in supersonic and hypersonic aircraft inner flow passage in practical application and the boundary layer separation that causes thus usually comparatively strong.For ensureing that intake duct can start smoothly, catching flow (even to 20%) just can play obvious control effects usually to need suction to fall greatly.This catches flow to intake duct and causes significant wastage, seriously constrains the overall performance of high-speed aircraft propulsion system.But, in fact in supersonic boundary layer, bottom low velocity zone only accounts for a very little part for whole boundary layer thickness, usually on distance wall 10% boundary layer thickness height and position, fluid mean velocity has reached more than 70% of mainstream speed, in addition supersonic boundary layer near-bottom temperature is higher, density is less, really needs the bottom low velocity fluid reality extracted only to account for a very little part for boundary layer mass flow rate in boundary layer suction controls.In the boundary layer Smoking regimes such as problem is traditional wall perforate, fluting is taken out, the most of gas flow extracted is actual to be derived from by the outside high velocity air extracted by mistake.This be due to traditional boundary layer suction method to boundary layer fluid carry out be indifference suction, namely the height near suction bole (or groove) position, bottom low velocity fluid are all aspirated, and it is poor to extract effect to bottom low velocity fluid in the boundary layer away from suction bole position.In this situation, have to increase overall aspiration for reaching specific boundary layer suction control effects, thus extracted quite a few high speed flow near suction bole, cause the significant wastage of effectively catching flow, and reduce overall engine performance.
Summary of the invention
The invention provides assisted border layer suction method in a kind of supersonic runner, with solve traditional wall perforate, fluting etc. directly the suction effect that exists of boundary layer suction mode poor, effectively catch the technical problem that flow waste is serious, restrict overall engine performance boost.
The invention provides assisted border layer suction method in a kind of supersonic runner, in supersonic runner, near wall region boundary layer fluid velocity inside outwards increases to Supersonic crossflow speed by zero gradually from wall, region near wall in supersonic runner is boundary layer fluid, the fluid being close to wall in boundary layer fluid is bottom low velocity fluid, fluid near Supersonic crossflow part in boundary layer fluid is upper strata high-velocity fluid, micropower thermoelectric generator is located at inside boundary, to be extracted by the bottom low velocity fluid of flow control technique by boundary layer, avoid because of the speed of the bottom low velocity fluid in boundary layer and energy too low and cause large scale flow separation, retain upper strata, boundary layer high-velocity fluid simultaneously, to lower flow loss.
Further, flow control technique comprises: the upstream incoming flow making to include boundary layer fluid by micropower thermoelectric generator while flow further downstream with the lifting gradually of micropower thermoelectric generator surface; By arranging sweepback edge in micropower thermoelectric generator upper surface both sides, come off with bottom low velocity fluid in the boundary layer making to move to sweepback edge and formed be rich in bottom low velocity fluid flow to whirlpool, thus reach the object that bottom low velocity fluid collects; Flow to whirlpool moves to micropower thermoelectric generator on the boundary layer under floor height speed fluid driven afterbody along the both sides sidewall of micropower thermoelectric generator; By arranging fluid extraction arrangement at micropower thermoelectric generator afterbody, with extract be passed to micropower thermoelectric generator afterbody be rich in bottom low velocity fluid flow to whirlpool, thus reach the object concentrated and extract bottom low velocity fluid in boundary layer.
Further, only there is the deviation of flow direction and do not come off in the boundary layer moving to micropower thermoelectric generator both sides sweepback adjacent edges at the middle and upper levels high-velocity fluid, thus walk around micropower thermoelectric generator and continue flow further downstream and do not extracted by mistake under extensional wave effect.
Further, micropower thermoelectric generator adopts the micropower thermoelectric generator of sweepback delta wing configuration; Sweepback delta wing has an incoming flow limit, and incoming flow limit is arranged perpendicular to the flow path direction that comes of boundary layer fluid, and the drift angle of the sweepback delta wing corresponding with incoming flow limit is arranged towards the flow downstream direction of boundary layer fluid.
Further, micropower thermoelectric generator in the form of an array close-packed arrays be arranged on the wall of supersonic runner.
Further, the separation boundary line in boundary layer between bottom low velocity fluid and upper strata high-velocity fluid is determined by inlet flow conditions and micropower thermoelectric generator structural characteristics.
Further, the vertical height h of sweepback delta wing is less than boundary layer thickness δ, inner to be controlled the zone of action of micropower thermoelectric generator at incoming flow boundary layer fluid, thus reduces boundary layer fluid in the extra aerodynamical resistance introduced in control procedure that flows.
Further, by changing the side chord length C of micropower thermoelectric generator and the semiapex angle angle A p of micropower thermoelectric generator, to change the division boundary line to bottom low velocity fluid and upper strata high-velocity fluid in the fluid boundary layer of boundary layer, and then change the ratio of boundary layer fluid shared by bottom low velocity fluid in the boundary layer that is collected, thus realize the control to being finally sucked bottom low velocity fluid flow in boundary layer that device extracts.
Further, by the angle at the sweepback angle at the semiapex angle angular adjustment sweepback edge of micropower thermoelectric generator, to adjust perpendicular to the velocity component in sweepback edge direction and vertical Mach-number component; 1.0 are greater than for boundary line, with the existence of extensional wave in the upper strata high-velocity fluid ensureing sweepback adjacent edges, and in this, as the criteria for classifying of upper strata high-velocity fluid and bottom low velocity fluid with vertical Mach-number component.
Further, the pump port of the aspirator funnel-shaped structure that adopts outer imperial palace that micropower thermoelectric generator afterbody can be avoided to occur that obvious fluid is separated little.
Further, the collar extension diameter of pump port matches with the diameter flowing to whirlpool, to ensure that the bottom low velocity fluid be collected can be extracted rapidly, effectively.
The present invention has following beneficial effect:
Utilize the bottom low velocity fluid of micropower thermoelectric generator uniqueness to collect effect to collect in advance the supersonic boundary layer bottom low velocity fluid that need extract, thus accurate, the efficient boundary layer of realization extracts.Compared with traditional indifference wall boundary layer suction mode, can ensure that while extracting boundary layer bottom low velocity fluid upper strata, boundary layer high-velocity fluid is unaffected, thus under the prerequisite reaching same boundary layer fluid momentum recovery level, the liquid mass flow extracted is needed greatly to reduce, mass flow rate loss even can be ignored, thus significantly improve the overall level of momentum in boundary layer with lower cost, improve boundary layer anti-reflective pressure energy power, suppress boundary layer separation.Thus the present invention will significantly improve the efficiency of wall Boundary layer flow, and reduces, because wall aspirates the mass flow rate loss caused, significantly to improve hypersonic/hypersonic aircraft intake duct startability and whole propulsion system performance.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the fundamental diagram of assisted border layer suction method in the supersonic runner of the preferred embodiment of the present invention;
Fig. 2 is the micropower thermoelectric generator configuration schematic diagram of the preferred embodiment of the present invention;
Fig. 3 is the micropower thermoelectric generator near side edges liquid speed decomposing schematic representation of the preferred embodiment of the present invention.
Marginal data:
1, boundary layer fluid; 2, micropower thermoelectric generator; 3, bottom low velocity fluid; 4, upper strata high-velocity fluid; 5, whirlpool is flowed to; 6, pump port; 7, aspirator.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the present invention can by the multitude of different ways that limits and cover implement.
Fig. 1 is the fundamental diagram of assisted border layer suction method in the supersonic runner of the preferred embodiment of the present invention; Fig. 2 is the micropower thermoelectric generator configuration schematic diagram of the preferred embodiment of the present invention; Fig. 3 is the micropower thermoelectric generator near side edges liquid speed decomposing schematic representation of the preferred embodiment of the present invention.
As shown in Figure 1, assisted border layer suction method in the supersonic runner of the present embodiment, in supersonic runner, near wall region boundary layer fluid velocity inside outwards increases to Supersonic crossflow speed by zero gradually from wall, region near wall in supersonic runner is boundary layer fluid 1, the fluid being close to wall in boundary layer fluid 1 is bottom low velocity fluid 3, fluid near Supersonic crossflow part in boundary layer fluid 1 is upper strata high-velocity fluid 4, micropower thermoelectric generator 2 is located at inside boundary, to be extracted by the bottom low velocity fluid 3 of flow control technique by boundary layer, avoid because of the speed of the bottom low velocity fluid 3 in boundary layer and energy too low and cause large scale flow separation, retain upper strata, boundary layer high-velocity fluid 4 simultaneously, to lower flow loss.Utilize the bottom low velocity fluid of micropower thermoelectric generator uniqueness to collect effect to collect in advance the supersonic boundary layer bottom low velocity fluid that need extract, thus accurate, the efficient boundary layer of realization extracts.Compared with traditional indifference wall boundary layer suction mode, can ensure that while extracting boundary layer bottom low velocity fluid upper strata, boundary layer high-velocity fluid is unaffected, thus under the prerequisite reaching same boundary layer fluid momentum recovery level, the liquid mass flow extracted is needed greatly to reduce, mass flow rate loss even can be ignored, thus significantly improve the overall level of momentum in boundary layer with lower cost, improve boundary layer anti-reflective pressure energy power, suppress boundary layer separation.Thus the present invention will significantly improve the efficiency of wall Boundary layer flow, and reduces, because wall aspirates the mass flow rate loss caused, significantly to improve hypersonic/hypersonic aircraft intake duct startability and whole propulsion system performance.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, flow control technique comprises: the upstream incoming flow making to include boundary layer fluid 1 by micropower thermoelectric generator 2 while flow further downstream with the lifting gradually of micropower thermoelectric generator 2 surface; By arranging sweepback edge in micropower thermoelectric generator 2 upper surface both sides, come off to make the boundary layer bottom low velocity fluid 3 moving to sweepback edge and formed be rich in bottom low velocity fluid 3 flow to whirlpool 5, thus reach the object that bottom low velocity fluid 3 collects; Flow to whirlpool 5 on the boundary layer layer high-velocity fluid 4 to move to the afterbody of micropower thermoelectric generator 2 under driving along the both sides sidewall of micropower thermoelectric generator 2; By arranging fluid extraction arrangement 7 at micropower thermoelectric generator 2 afterbody, with extract be passed to micropower thermoelectric generator 2 afterbody be rich in bottom low velocity fluid 3 flow to whirlpool 5, thus reach the object concentrated and extract bottom low velocity fluid 3 in boundary layer.
Assisted border layer suction method in the supersonic runner of the present embodiment, micropower thermoelectric generator 2 is in the bottom of supersonic runner near wall region incoming flow boundary layer fluid 1, and the boundary layer fluid 1 (comprising bottom low velocity fluid 3 and upper strata high-velocity fluid 4) that micropower thermoelectric generator 2 makes to flow through it is with its upper surface micro-lifting move to its near side edges gradually; The side margin of micropower thermoelectric generator 2 upper surface sweepback makes motion bottom low velocity fluid 3 so far come off and be formed and flows to whirlpool 5, flow to whirlpool 5 and sweep along bottom low velocity fluid 3 to move to the afterbody of micropower thermoelectric generator 2 along the sidewall of micropower thermoelectric generator 2, originally the bottom low velocity fluid 3 being in boundary layer bottom from effect is all collected in vortex generator afterbody after flowing through micropower thermoelectric generator 2, thus reaches bottom low velocity fluid pre-collecting effect; Then by the fluid extraction arrangement 7 that is arranged on micropower thermoelectric generator 2 afterbody to transmit so far flow to whirlpool 5 and the bottom low velocity fluid that comprises is concentrated, is extracted efficiently; Meanwhile, the upper strata high-velocity fluid 4 in boundary layer directly can not come off at vortex generator side margin, but under extensional wave effect, flow to deviation and walk around the continuation of micropower thermoelectric generator 2 side margin to downstream movement, the new boundary layer of forming energy higher level, reaching flowing and controlling object.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, only there is the deviation of flow direction and do not come off in the boundary layer moving to micropower thermoelectric generator 2 both sides sweepback adjacent edges at the middle and upper levels high-velocity fluid 4, thus walk around micropower thermoelectric generator 2 and continue flow further downstream and do not extracted by mistake under extensional wave effect.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, micropower thermoelectric generator 2 adopts the micropower thermoelectric generator of sweepback delta wing configuration; Sweepback delta wing has an incoming flow limit, and incoming flow limit is arranged perpendicular to the flow path direction that comes of boundary layer fluid 1, and the drift angle of the sweepback delta wing corresponding with incoming flow limit is arranged towards the flow downstream direction of boundary layer fluid 1.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, micropower thermoelectric generator 2 in the form of an array close-packed arrays is arranged on the wall of supersonic runner.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the boundary line in boundary layer between bottom low velocity fluid 3 and upper strata high-velocity fluid 4 is determined jointly by inlet flow conditions and micropower thermoelectric generator 2 structural characteristics.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the vertical height h of sweepback delta wing is less than boundary layer thickness δ, inner to be controlled the zone of action of micropower thermoelectric generator 2 at incoming flow boundary layer fluid 1, thus reduces boundary layer fluid 1 in the extra aerodynamical resistance introduced in control procedure that flows.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, by changing the side chord length C of the micropower thermoelectric generator 2 and semiapex angle angle A p of micropower thermoelectric generator 2, to change the division boundary line to bottom low velocity fluid 3 and upper strata high-velocity fluid 4 in boundary layer fluid 1, and then change the ratio of boundary layer fluid 1 shared by the boundary layer bottom low velocity fluid 3 that is collected, thus realize the control being finally sucked boundary layer bottom low velocity fluid 3 flow that device 7 extracts.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, by the angle at the sweepback angle at the semiapex angle angular adjustment sweepback edge of micropower thermoelectric generator 2, to adjust perpendicular to the velocity component U in sweepback edge direction
nwith corresponding vertical Mach-number component.1.0 are greater than for boundary line, with the existence of extensional wave in the upper strata high-velocity fluid 4 ensureing sweepback adjacent edges, and in this, as the criteria for classifying of upper strata high-velocity fluid 4 with bottom low velocity fluid 3 with vertical Mach-number component.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the funnel-shaped structure that the pump port 6 of aspirator 7 adopts outer imperial palace that micropower thermoelectric generator 2 afterbody can be avoided to occur that obvious fluid is separated little.
As shown in Figure 1, Figure 2 and Figure 3, the collar extension diameter of pump port 6 matches with the diameter flowing to whirlpool 5, to ensure that the bottom low velocity fluid 3 be collected can be extracted rapidly, effectively.
During enforcement, the present invention relates to the assisted border layer suction method in a kind of supersonic runner.Its principle is before supersonic boundary layer suction, utilize nearly wall fluid micropower thermoelectric generator 2 side margin come off formed wake flow layering the bottom low velocity fluid 3 bottom supersonic boundary layer is collected in advance, subsequently to the low speed flow collected in wake flow carry out concentrate suction.From effect, the present invention distributed adjust in advance the upper strata high-velocity fluid 4 of boundary layer fluid 1, bottom low velocity fluid 3 before boundary layer suction is implemented, concentrate within the very little region of micropower thermoelectric generator 2 tail end by really needing the bottom low velocity fluid 3 of the nearly wall extracted in boundary layer suction, and then carry out concentrating suction, realize the accurate suction of the bottom low velocity fluid 3 to wall boundary layer.Compared with traditional indifference wall boundary layer suction mode, can ensure that while extracting boundary layer bottom low velocity fluid 3 upper strata, boundary layer high-velocity fluid 4 is unaffected, thus under the prerequisite reaching same boundary layer fluid 1 momentum recovery level, need the liquid mass flow extracted greatly to reduce, mass flow rate loss even can be ignored.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. an assisted border layer suction method in supersonic runner,
In supersonic runner, near wall region boundary layer fluid velocity inside outwards increases to Supersonic crossflow speed by zero gradually from wall,
Region near wall in described supersonic runner is boundary layer fluid (1),
In described boundary layer fluid (1), the fluid of next-door neighbour's wall is bottom low velocity fluid (3), and the fluid near Supersonic crossflow part in described boundary layer fluid (1) is upper strata high-velocity fluid (4),
It is characterized in that,
Micropower thermoelectric generator (2) is located at inside boundary, to be extracted by the described bottom low velocity fluid (3) of flow control technique by boundary layer, avoid because of the speed of the bottom low velocity fluid (3) in boundary layer and energy too low and cause large scale flow separation, retain the upper strata high-velocity fluid (4) in boundary layer, to lower flow loss simultaneously;
Described flow control technique comprises: the upstream incoming flow making to include described boundary layer fluid (1) by described micropower thermoelectric generator (2) while flow further downstream with the lifting gradually of described micropower thermoelectric generator (2) surface;
By arranging sweepback edge in described micropower thermoelectric generator (2) upper surface both sides, come off to make the described bottom low velocity fluid (3) in the boundary layer moving to sweepback edge and formed be rich in described bottom low velocity fluid (3) flow to whirlpool (5), thus reach the object that bottom low velocity fluid (3) collects;
Describedly flow to the afterbody moving to described micropower thermoelectric generator (2) under the upper strata high-velocity fluid (4) of whirlpool (5) in boundary layer drives along the both sides sidewall of described micropower thermoelectric generator (2);
By arranging fluid extraction arrangement (7) at described micropower thermoelectric generator (2) afterbody, flow to whirlpool (5) to extract the described of described bottom low velocity fluid (3) of being rich in being passed to described micropower thermoelectric generator (2) afterbody, thus reach the object concentrated and extract the low velocity fluid of bottom described in boundary layer (3).
2. assisted border layer suction method in supersonic runner according to claim 1, is characterized in that,
Described in the boundary layer moving to described micropower thermoelectric generator (2) both sides sweepback adjacent edges only there is the deviation of flow direction and do not come off in upper strata high-velocity fluid (4) under extensional wave effect, thus walk around described micropower thermoelectric generator (2) and continue flow further downstream and do not extracted by mistake.
3. assisted border layer suction method in supersonic runner according to claim 1, is characterized in that,
Described micropower thermoelectric generator (2) adopts the micropower thermoelectric generator of sweepback delta wing configuration;
Described sweepback delta wing has an incoming flow limit,
Described incoming flow limit is arranged perpendicular to the flow path direction that comes of described boundary layer fluid (1),
The drift angle of the sweepback delta wing corresponding with described incoming flow limit is arranged towards the flow downstream direction of described boundary layer fluid (1).
4. assisted border layer suction method in supersonic runner according to claim 3, is characterized in that,
Described micropower thermoelectric generator (2) in the form of an array close-packed arrays is arranged on the wall of described supersonic runner.
5. assisted border layer suction method in supersonic runner according to claim 3, is characterized in that,
Boundary line between the described bottom low velocity fluid (3) in boundary layer and described upper strata high-velocity fluid (4) in boundary layer is determined by inlet flow conditions and described micropower thermoelectric generator (2) structural characteristics.
6. assisted border layer suction method in supersonic runner according to claim 5, is characterized in that,
The vertical height h of described sweepback delta wing is less than boundary layer thickness δ, inner the zone of action of described micropower thermoelectric generator (2) to be controlled boundary layer fluid (1) described in incoming flow, thus reduce described boundary layer fluid (1) in the extra aerodynamical resistance introduced in control procedure that flows.
7. assisted border layer suction method in supersonic runner according to claim 5, is characterized in that,
By the semiapex angle angle A p of the side chord length C and described micropower thermoelectric generator (2) that change described micropower thermoelectric generator (2), to change the division boundary line to bottom low velocity fluid (3) described in described boundary layer fluid (1) and described upper strata high-velocity fluid (4)
And then change the ratio of the shared described boundary layer fluid (1) of bottom low velocity fluid (3) described in the boundary layer that is collected, thus realize the control to bottom low velocity fluid (3) flow described in the boundary layer finally extracted by described aspirator (7).
8. assisted border layer suction method in supersonic runner according to claim 7, is characterized in that,
By the angle at the sweepback angle at the semiapex angle angular adjustment sweepback edge of described micropower thermoelectric generator (2), to adjust perpendicular to the velocity component in sweepback edge direction and vertical Mach-number component;
1.0 are greater than for boundary line with vertical Mach-number component, to ensure the existence of the middle extensional wave in described upper strata high-velocity fluid (4) of sweepback adjacent edges, and in this, as the criteria for classifying of described upper strata high-velocity fluid (4) with described bottom low velocity fluid (3).
9. assisted border layer suction method in supersonic runner according to any one of claim 1 to 8, is characterized in that,
The funnel-shaped structure that the pump port (6) of described aspirator (7) adopts outer imperial palace that described micropower thermoelectric generator (2) afterbody can be avoided to occur that obvious fluid is separated little.
10. assisted border layer suction method in supersonic runner according to claim 9, is characterized in that,
The collar extension diameter of described pump port (6) matches with the diameter flowing to whirlpool (5), to ensure that the described bottom low velocity fluid (3) be collected can be extracted rapidly, effectively.
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| CN112173082A (en) * | 2020-08-25 | 2021-01-05 | 中国航天空气动力技术研究院 | Micro-vortex generating device with auxiliary control of airflow |
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| CN112173082B (en) * | 2020-08-25 | 2021-11-16 | 中国航天空气动力技术研究院 | Micro-vortex generating device with auxiliary control of airflow |
| CN113062802A (en) * | 2021-04-09 | 2021-07-02 | 北京航空航天大学 | Suction type air inlet channel for separating boundary layer and modeling method thereof |
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| CN105257635B (en) | 2018-03-16 |
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