CN106394874B - A kind of Waverider of double sweepback layouts - Google Patents
A kind of Waverider of double sweepback layouts Download PDFInfo
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- CN106394874B CN106394874B CN201610912726.1A CN201610912726A CN106394874B CN 106394874 B CN106394874 B CN 106394874B CN 201610912726 A CN201610912726 A CN 201610912726A CN 106394874 B CN106394874 B CN 106394874B
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- waverider
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- costa
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
Abstract
A kind of Waverider of double sweepback layouts, the upper surface of the Waverider is the plane that free stream interface is tracked, and lower surface is the curved surface with rider performance, which is described by blunt nosed region, big sweepback angular zone and low sweep angle region；Wherein, blunt nosed region for Waverider design in streamlined impeller curved surface, cut rate of the Blunt leading edge line at symmetry axis is zero；Big sweepback angular zone is also referred to as inboard wing portion, it is smoothly connected in the two sides in blunt nosed region, its outer mold surface is made of costa and curve, costa is big sweepback straight line, 50 ° -80 ° of sweepback angular region, and the distance between costa end and blunt nosed edges of regions be less than half length of Waverider 30%, curve for Waverider design in streamlined impeller line；Low sweep angle region is also referred to as outer wing part, is smoothly connected in the streamline two sides of big sweepback angular zone, the costa in low sweep angle region is straight line, 30 ° -70 ° of angle of sweep.
Description
Technical field
The present invention relates to hypersonic aircraft pneumatic design fields, especially Waverider distribution form.
Background technique
High-lift supersonic speed/hypersonic shape is always the unremitting pursuit of the mankind.According to hypersonic frictionless flow
The aeroperformance of Hyperbolic Feature, aircraft can be largely improved, and Waverider is exactly to utilize this characteristic
Representative configuration.High-pressure pneumatic is segmented in aircraft lower surface by attachment shock wave and prevents flowing leakage by Waverider, is effectively broken through
The liter of hypersonic aircraft hinders barrier, has very high lift resistance ratio.After decades of development, list of the Waverider from early stage
It is the complex configuration with different characteristics that one configuration, which gradually develops, especially the proposition of cone method closely, can be swashed by given
Wave exports molded line and carries out Waverider design, the Waverider shape with more characteristics.
The engineer application of Waverider still has many limitations at present, main problem include lower-speed state aeroperformance not
Good, longitudinal stability is difficult to ensure.Waverider shape is generally obtained according to Hypersonic Flow Field by streamlined impeller, is generated
Curved surface has unique feature, it is difficult to it freely designs, but the flat shape of Waverider can be modified by design curve, this
Improve Waverider for us and provide a kind of thinking highly considered in the aeroperformance of off-design point, depending on angle of sweep multiply
The concept of wave body then provides effective way for this thinking.It is long-standing to determine angle of sweep Waverider, but only other in early days
" accessory " of type Waverider.In recent years, related scholar proposes from close cone Waverider design method and determines angle of sweep
The concept of cone and close flow field Waverider closely.This conception of species improves the flexibility of Waverider design method, but multiplies in improvement
Application in terms of wave volume defect is also less.
Summary of the invention
Technology of the invention solves the problems, such as: overcome general Waverider shape low-speed performance poor, longitudinal stability is bad etc.
Disadvantage provides a kind of Waverider of double sweepback layouts.
The technical solution of the invention is as follows: a kind of Waverider of double sweepback layouts, the upper surface of the Waverider is
The plane that free stream interface is tracked, lower surface are the curved surface with rider performance, which passes through blunt nosed region, big angle of sweep
Region and low sweep angle region are described；Wherein, blunt nosed region for Waverider design in streamlined impeller curved surface, Blunt leading edge
Cut rate of the line at symmetry axis is zero；Big sweepback angular zone is also referred to as inboard wing portion, is smoothly connected in the two sides in blunt nosed region, outside
Type face is made of costa and curve, costa be big sweepback straight line, 50 ° -80 ° of sweepback angular region, and costa end with it is blunt
The distance between head region edge be less than half length of Waverider 30%, curve for Waverider design in streamlined impeller line；It is small
Sweepback angular zone is also referred to as outer wing part, is smoothly connected in the streamline two sides of big sweepback angular zone, the leading edge in low sweep angle region
Line is straight line, 30 ° -70 ° of angle of sweep.
Blunt nosed region is led using cone to be set as horizontal linear for streamlined impeller initial line in rider body method and obtains.
Blunt nosed region, which uses, sets shock wave outlet molded line as circular arc in close cone method, set streamlined impeller initial line as water
Flat line obtains.
Low sweep angle region, which uses, sets shock wave outlet molded line as straight line in close cone method, set the stream in osculating plane
Field is supersonic speed wedge shape flow field, sets streamlined impeller initial line and obtains as horizontal linear.
The slope inclination angle of the shock wave outlet molded line in low sweep angle region is less than the circle of blunt nosed region shock wave outlet molded line circular arc
Heart angle.
Big sweepback angular zone designs to obtain using close cone method, wherein setting shock wave exports molded line to connect blunt nosed region
Shock wave outlet molded line is denoted as curve A and low sweep angle region shock wave outlet molded line is denoted as the smoothed curve of curve B, the smoothed curve
Curvature be set as linearly being reduced to the curvature of curve B from the curvature of curve A；Streamlined impeller initial line is set as horizontal linear.
The smoothed curve is expressed using B-spline method, to guarantee the slickness of transitional region.
The angle of sweep size of low sweep angle region costa is optimal to choose the angle of sweep for being less than big sweepback angular zone.
The angle of sweep size of low sweep angle region costa is optimal less than 60 °.
The distance of blunt nosed region costa outermost end to symmetry axis is no more than the 40% of half length of Waverider.
The present invention has the beneficial effect that compared with prior art
(1) double sweepback Waveriders are maintained hypersonic by the big sweepback region in building inside and the small sweepback region in outside
The high lift-drag ratio performance in stage, while aspect ratio is increased from geometrically whole, have the aeroperformance of lower-speed state very big
It is promoted.
(2) by reducing outer wing part angle of sweep, pneumatic retrofocus can be made, enhance longitudinal stability.
(3) present invention designs blunt nosed region, low sweep angle region and big sweepback angular zone and then determines Waverider shape, real
The customization design for having showed Waverider, keeps design method more flexible.
Detailed description of the invention
Fig. 1 is the double sweepback Waverider outline drawings of the present invention (following table is face-up)；
Fig. 2 is the double sweepback Waverider plan views of the present invention；
Fig. 3 is present invention cone Waverider design method schematic diagram closely；
Fig. 4 is the double sweepback Waverider design method schematic diagrames of the present invention；
Fig. 5 is the double sweepback shape lower surface isobars of the present invention；
Fig. 6 is influence of the angle of sweep of the present invention to low-speed performance；
Fig. 7 is influence of the angle of sweep of the present invention to longitudinal stability.
Specific embodiment
Design principle of the present invention: separately designing the rider body portion with different characteristic, and combination obtains double sweepback features and multiplies
Wave body distribution form, including blunt nosed region, big sweepback angular zone and low sweep angle region, A as shown in figure 1, B, the region C.Fig. 2 gives
Flat shape figure is gone out, wherein l1,l2,l3The respectively costa in above three region, λ1And λ2Respectively big sweepback angular zone
With the angle of sweep in low sweep angle region.Such shape Waverider is with the advantage in terms of lower-speed state performance and longitudinal stability.
Blunt nosed region can be led by cone or the method for boring obtains closely, other regions are then obtained by close cone method.
The design principle of cone Waverider closely is briefly introduced, as shown in figure 3, the outlet molded line using ICC curve as shock wave,
It is taken on ICC curve and a little makees tangent line, be called osculating plane perpendicular to the plane of this tangent line, by the radius of curvature when place close
Taper flow field is fitted in tangent plane.FCT is projected into shock wave as the initial point of tracking and carries out streamlined impeller, is generated under Waverider
Surface.Upper surface generally carries out streamlined impeller using free-flowing and obtains.Specific above-mentioned trizonal design passes through following sides
Formula obtains:
(1) blunt nosed region
When leading rider body method using cone, streamlined impeller initial line is set as horizontal linear.
When using close cone method, shock wave outlet molded line is set as circular arc, sets streamlined impeller initial line as horizontal linear
It obtains.
(2) low sweep angle region
Low sweep angle region, which uses, sets shock wave outlet molded line as straight line in close cone method, set the stream in osculating plane
Field is supersonic speed wedge shape flow field, sets streamlined impeller initial line and obtains as horizontal linear.
The slope inclination angle theta of the shock wave outlet molded line in low sweep angle region2Less than blunt nosed region shock wave outlet molded line circular arc
Central angle θ1。
(3) big sweepback angular zone
It designs to obtain using close cone method, exports molded line to connect blunt nosed region shock wave wherein setting shock wave and exporting molded line
It is denoted as curve A and low sweep angle region shock wave outlet molded line is denoted as the smoothed curve of curve B, the curvature of the smoothed curve is set as
The curvature of curve B is linearly reduced to from the curvature of curve A；Streamlined impeller initial line is set as horizontal linear.Smoothed curve uses B
Spline method expression, to guarantee the slickness of transitional region.
After the completion of design, Waverider of the present invention is as shown in Figure 1, the upper surface of Waverider is put down for what free stream interface was tracked
Face, lower surface be the curved surface with rider performance, the curved surface by blunt nosed region, big sweepback angular zone and low sweep angle region into
Row description；Wherein, blunt nosed region for Waverider design in streamlined impeller curved surface, cut rate of the Blunt leading edge line at symmetry axis be
Zero；Big sweepback angular zone is also referred to as inboard wing portion, is smoothly connected in the two sides in blunt nosed region, outer mold surface is by costa and curve group
It is big sweepback straight line at, costa, 50 ° -80 ° of sweepback angular region, and the distance between costa end and blunt nosed edges of regions
Less than the 30% of half length of Waverider, curve for Waverider design in streamlined impeller line；Low sweep angle region is also referred to as outer wing
Part is smoothly connected in the streamline two sides of big sweepback angular zone, and the costa in low sweep angle region is straight line, angle of sweep
30°-70°.The angle of sweep size of low sweep angle region costa is optimal to choose the angle of sweep for being less than big sweepback angular zone.Blunt nosed area
The distance of domain costa outermost end to symmetry axis is no more than the 40% of half length of Waverider.
Fig. 4 gives the design diagram in three parts region, and circular arc AB is that the shock wave of the design in blunt nosed region exports molded line,
Central angle θ1, curve BC is that the shock wave of big sweepback angular zone exports molded line, and straight line CD is that the shock wave in small sweepback region exports molded line,
Slope inclination angle is θ2。
This double sweepback Waverider is kept in the high lift-drag ratio characteristic of hypersonic state.Use Fluid Mechanics Computation
(CFD) method carries out verifying calculating, double sweepback Waverider lower surface isobar distributions when Fig. 5 is Ma6, it can be seen that shock wave attachment
In lower surface, the leakage flowed from lower surface to upper surface is limited, there is rider characteristic.
Double sweepback Waveriders have performance advantage in terms of low speed, and Fig. 6 gives when inboard wing portion angle of sweep is 70 °,
Change outboard wing sweep (70-30 °) in Ma=0.4 lift resistance ratio L/D with angle of attack variation, it can be seen that with outer wing part
The reduction at angle of sweep, the lift resistance ratio of Waverider has significantly to be promoted very much.
Double sweepback Waveriders improve longitudinal stability, and it is 70 ° that Fig. 7 (left side), which gives given inboard wing portion angle of sweep, change
When becoming outboard wing sweep (70-30 °), torque C under hypersonic statemWith the variation of the angle of attack, when outer wing part angle of sweep reduces
When, steady state stability increases.In the initial design stage of aerodynamic arrangement, position of centre of gravity is difficult to determine sometimes, can be vertical by calculating
The static-stability characteristic of aircraft is judged with the variation of the angle of attack to pressure heart position.Fig. 7 (right side) gives Center of Pressure Pr Ct with attacking
The change curve at angle, in such cases when outboard wing sweep is less than 60 °, with the angle of attack increase pressure heart position move back, the angle of attack by
Restoring moment can be generated after changing to disturbance, ensure that the Longitudinal static stability under flying condition.And outboard wing sweep compared with
When big, Center of Pressure Forward, static stability cannot be guaranteed.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (10)
1. a kind of Waverider of double sweepback layouts, it is characterised in that: the upper surface of the Waverider is that free stream interface is tracked
The plane arrived, lower surface are the curved surface with rider performance, which passes through blunt nosed region, big sweepback angular zone and low sweep angle
Region is described；Wherein, blunt nosed region for Waverider design in streamlined impeller curved surface, Blunt leading edge line is at symmetry axis
The rate of cutting is zero；Big sweepback angular zone is also referred to as inboard wing portion, is smoothly connected in the two sides in blunt nosed region, outer mold surface by costa and
Curve composition, costa are big sweepback straight line, 50 ° -80 ° of sweepback angular region, and between costa end and blunt nosed edges of regions
Distance be less than half length of Waverider 30%, curve for Waverider design in streamlined impeller line；Low sweep angle region is also referred to as
For outer wing part, it is smoothly connected in the streamline two sides of big sweepback angular zone, the costa in low sweep angle region is straight line, after
30 ° -70 ° of sweep angle.
2. a kind of Waverider of double sweepback layouts according to claim 1, it is characterised in that: blunt nosed region is led using cone to be multiplied
Streamlined impeller initial line is set as horizontal linear in wave body method to obtain.
3. a kind of Waverider of double sweepback layouts according to claim 1, it is characterised in that: blunt nosed region is using cone closely
Shock wave outlet molded line is set in method as circular arc, is set streamlined impeller initial line and is obtained as horizontal linear.
4. a kind of Waverider of double sweepback layouts according to claim 1 or 2 or 3, it is characterised in that: low sweep angle region
It uses and sets shock wave outlet molded line in close cone method as straight line, set the flow field in osculating plane as supersonic speed wedge shape flow field,
Streamlined impeller initial line is set to obtain as horizontal linear.
5. a kind of Waverider of double sweepback layouts according to claim 4, it is characterised in that: the shock wave in low sweep angle region
The slope inclination angle for exporting molded line is less than the central angle of blunt nosed region shock wave outlet molded line circular arc.
6. a kind of Waverider of double sweepback layouts according to claim 1, it is characterised in that: big sweepback angular zone is using close
Cone of tangents method designs to obtain, wherein setting shock wave outlet molded line to connect blunt nosed region shock wave outlet molded line and being denoted as curve A and small
Sweepback angular zone shock wave outlet molded line is denoted as the smoothed curve of curve B, and the curvature of the smoothed curve is set as the curvature from curve A
Linearly it is reduced to the curvature of curve B；Streamlined impeller initial line is set as horizontal linear.
7. a kind of Waverider of double sweepback layouts according to claim 6, it is characterised in that: the smoothed curve uses
B-spline method expression, to guarantee the slickness of transitional region.
8. a kind of Waverider of double sweepback layouts according to claim 1, it is characterised in that: low sweep angle region costa
Angle of sweep be less than big sweepback angular zone angle of sweep.
9. a kind of Waverider of double sweepback layouts according to claim 8, it is characterised in that: low sweep angle region costa
Angle of sweep less than 60 °.
10. a kind of Waverider of double sweepback layouts according to claim 1, it is characterised in that: blunt nosed region costa is most
The distance of outer end to symmetry axis is no more than the 40% of half length of Waverider.
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| CN201610912726.1A CN106394874B (en) | 2016-10-19 | 2016-10-19 | A kind of Waverider of double sweepback layouts |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107253521B (en) * | 2017-07-03 | 2019-12-24 | 中国空气动力研究与发展中心计算空气动力研究所 | Curve head double-sweepback osculating wave multiplier with transition section |
| CN107298162B (en) * | 2017-07-03 | 2019-11-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Waverider is bored in a kind of double sweepback of the sharp apex with changeover portion closely |
| CN108502204B (en) * | 2018-04-03 | 2020-11-24 | 北京航空航天大学 | Hypersonic speed combined wedge waverider design method |
| CN111152909A (en) * | 2019-11-12 | 2020-05-15 | 湖南云顶智能科技有限公司 | Projection method based double-sweepback waverider design method for determining plane shape |
| CN111688905B (en) * | 2020-06-10 | 2023-03-24 | 中国空气动力研究与发展中心 | Double-sweepback waverider design method for streamline tracking axial-symmetry curved surface conical flow field |
| CN112389626A (en) * | 2020-10-29 | 2021-02-23 | 中国航天空气动力技术研究院 | High super aerodynamic overall arrangement in integrative fixed wing span of sharp leading edge vortex |
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