CN106394874A - Wave rider of dual sweepback layout - Google Patents
Wave rider of dual sweepback layout Download PDFInfo
- Publication number
- CN106394874A CN106394874A CN201610912726.1A CN201610912726A CN106394874A CN 106394874 A CN106394874 A CN 106394874A CN 201610912726 A CN201610912726 A CN 201610912726A CN 106394874 A CN106394874 A CN 106394874A
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- sweepback
- waverider
- region
- line
- angle
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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
The invention relates to a wave rider of dual sweepback layout. The upper surface of the wave rider is a plane capable of being tracked by a free stream surface, the lower surface of the wave rider is a curved surface with wave rider performance, and the curved surface is described through a blunt end area, large sweepback areas and small sweepback areas. The blunt end area is a streamline tracking curved surface in wave rider design, and the cut rate of a blunt end leading edge line on an axis of symmetry is zero. The large sweepback areas are also called inner wing parts and are smoothly connected to the two sides of the blunt end area, and the outer profile of each large sweepback area is composed of a leading edge line and a curve; each leading edge line is a large sweepback straight line, and the sweepback ranges from 50 degrees to 80 degrees; and the distance between the tail end of each leading edge line and the edge of the blunt end area is smaller than 30% of the half elongation of the wave rider, and each curve is a streamline tracking line in wave rider design. The small sweepback areas are also called outer wing parts and are smoothly connected to the two sides of the streamlines of the large sweepback areas, a leading edge line of each small sweepback area is a straight line, and the sweepback ranges from 30 degrees to 70 degrees.
Description
Technical field
The present invention relates to hypersonic aircraft pneumatic design field, particularly Waverider distribution form.
Background technology
High-lift supersonic speed/hypersonic profile is always the unremitting pursuit of the mankind.According to hypersonic frictionless flow
Hyperbolic Feature, the aeroperformance of aircraft can be improved to a great extent, and Waverider is using this characteristic
Representative configuration.High-pressure pneumatic is segmented in the prevention flowing leakage of aircraft lower surface by adhering to shock wave by Waverider, effectively breaks through
The liter resistance barrier of hypersonic aircraft, has a very high lift-drag ratio.Through the development of decades, Waverider is from the list of early stage
One configuration gradually develops into the complex configuration with different characteristics, especially closely bores the proposition of method, can be swashed by given
Ripple outlet molded line carries out Waverider design, has the Waverider profile of more characteristics.
The engineer applied of Waverider still has many restrictions at present, and subject matter includes lower-speed state aeroperformance not
Good, longitudinal stability is difficult to ensure that.Waverider profile is typically based on Hypersonic Flow Field and is obtained by streamlined impeller, its generation
Curved surface has the feature of uniqueness it is difficult to freely design, but the flat shape of Waverider can be modified by design curve, this
Improve Waverider for us and provide a kind of thinking highly considering in the aeroperformance of off-design point, depending on angle of sweep take advantage of
The concept of ripple body then provides effective way for this thinking.Determine angle of sweep Waverider long-standing, but be other in early stage
" accessory " of type Waverider.In recent years, related scholar from close cone Waverider method for designing it is proposed that determining angle of sweep
Closely bore the concept with close flow field Waverider.This conception of species improves the motility of Waverider method for designing, but takes advantage of in improvement
The application of ripple volume defect aspect is also less.
Content of the invention
The technology solve problem of the present invention is：Overcome general Waverider profile low-speed performance is poor, and longitudinal stability is bad etc.
Shortcoming, provides the Waverider of a kind of pair of sweepback layout.
The technical solution of the present invention is：The Waverider of a kind of pair of sweepback layout, the upper surface of described Waverider is
The plane that free stream interface tracking obtains, lower surface is the curved surface with rider performance, and this curved surface passes through blunt nosed region, big angle of sweep
Region and low sweep angle region are described；Wherein, the streamlined impeller curved surface during blunt nosed region is designed for Waverider, Blunt leading edge
The rate of cutting at axis of symmetry for the line is zero；Big sweepback angular zone is also referred to as inboard wing portion, in smoothing junction in the both sides in blunt nosed region, outside it
Type face is made up of costa and curve, costa be big sweepback straight line, 50 ° -80 ° of sweepback angle range, and costa end with blunt
The distance between head region edge be less than Waverider half length 30%, curve design for Waverider in streamlined impeller line；Little
Sweepback angular zone is also referred to as outer wing part, and smooth connection is in the streamline both 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 in rider body method using cone and for streamlined impeller initial line to be set as that horizontal linear obtains.
Blunt nosed region adopts and sets shock wave outlet molded line in close cone method as circular arc, sets streamlined impeller initial line as water
Flat line obtains.
Low sweep angle region adopts and sets shock wave outlet molded line in close cone method as straight line, sets 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 that the shock wave in low sweep angle region exports molded line is less than the circle that blunt nosed region shock wave exports molded line circular arc
Heart angle.
Big sweepback angular zone is obtained using the design of close cone method, wherein sets shock wave outlet molded line as connecting blunt nosed region
Shock wave outlet molded line is designated as curve A and low sweep angle region shock wave exports the smoothed curve that molded line is designated as curve B, this smoothed curve
Curvature be set as linearly being reduced to the curvature of curve B from the curvature of curve A；Set streamlined impeller initial line as horizontal linear.
Described smoothed curve adopts B-spline method to express, to ensure the slickness of transitional region.
The optimum angle of sweep chosen less than big sweepback angular zone of angle of sweep size of low sweep angle region costa.
The angle of sweep size of low sweep angle region costa is optimum to be less than 60 °.
The distance of blunt nosed region costa outermost end to axis of symmetry is less than the 40% of Waverider half length.
The present invention compared with prior art has the beneficial effect that：
(1) double sweepback Waveriders pass through to build the big sweepback region in inner side and outside little sweepback region, maintain hypersonic
The high lift-drag ratio performance in stage, increased aspect ratio from geometrically overall simultaneously, so that the aeroperformance of lower-speed state is had very big
Lifting.
(2) pass through to reduce 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 profile, real
Show the customization design of Waverider, made method for designing more flexible.
Brief description
Fig. 1 is double sweepback Waverider outline drawing (following table faces up) of the present invention；
Fig. 2 is the double sweepback Waverider plane graph of the present invention；
Fig. 3 bores Waverider method for designing schematic diagram closely for the present invention；
Fig. 4 is the double sweepback Waverider method for designing schematic diagram of the present invention；
Fig. 5 is the double sweepback profile lower surface isobar of the present invention；
Fig. 6 is the impact to low-speed performance for the angle of sweep of the present invention；
Fig. 7 is the impact to longitudinal stability for the angle of sweep of the present invention.
Specific embodiment
Design principle of the present invention：Separately design the rider body portion with different characteristic, combination obtains double sweepback features and takes advantage of
Ripple body distribution form, including blunt nosed region, big sweepback angular zone and low sweep angle region, the A in such as Fig. 1, B, C region.Fig. 2 gives
Flat shape figure, wherein l are gone out1,l2,l3It is respectively the costa in above three region, λ1And λ2It is respectively big sweepback angular zone
Angle of sweep with low sweep angle region.This kind of profile Waverider has lower-speed state performance and the advantage of longitudinal stability aspect.
Blunt nosed region can be led by cone or cone method closely obtains, and other regions are then obtained by close cone method.
Briefly introduce the design principle closely boring Waverider, as shown in figure 3, using ICC curve as the outlet molded line of shock wave,
ICC curve takes and a little makees tangent line, the plane perpendicular to this tangent line is called osculating plane, by the radius of curvature when place close
Matching taper flow field in incisal plane.FCT is projected to shock wave and carry out streamlined impeller as the initial point followed the trail of, generate under Waverider
Surface.Upper surface typically carries out streamlined impeller using free-flowing and obtains.Specifically following sides are passed through in above-mentioned trizonal design
Formula obtains：
(1) blunt nosed region
When rider body method is led using cone, streamlined impeller initial line is set as horizontal linear.
During using close cone method, set shock wave outlet molded line as circular arc, set streamlined impeller initial line as horizontal linear
Obtain.
(2) low sweep angle region
Low sweep angle region adopts and sets shock wave outlet molded line in close cone method as straight line, sets the stream in osculating plane
Field is supersonic speed wedge shape flow field, sets streamlined impeller initial line and obtains as horizontal linear.
The shock wave in low sweep angle region exports the slope inclination angle theta of molded line2Export molded line circular arc less than blunt nosed region shock wave
Central angle θ1.
(3) big sweepback angular zone
Obtained using the design of close cone method, wherein set shock wave outlet molded line as connecting blunt nosed region shock wave outlet molded line
It is designated as curve A and low sweep angle region shock wave exports the smoothed curve that molded line is designated as curve B, the curvature of this smoothed curve is set as
Linearly it is reduced to the curvature of curve B from the curvature of curve A；Set streamlined impeller initial line as horizontal linear.Smoothed curve adopts B
Spline method is expressed, to ensure the slickness of transitional region.
After the completion of design, Waverider of the present invention follows the trail of, as shown in figure 1, the upper surface of Waverider is free stream interface, obtain flat
Face, lower surface is the curved surface with rider performance, and this curved surface is entered by blunt nosed region, big sweepback angular zone and low sweep angle region
Row description；Wherein, the streamlined impeller curved surface during blunt nosed region is designed for Waverider, the rate of cutting at axis of symmetry for the Blunt leading edge line is
Zero；Big sweepback angular zone is also referred to as inboard wing portion, and in the both sides in blunt nosed region, its outer mold surface is by costa and curve group for smooth connection
Become, costa is the distance between big sweepback straight line, 50 ° -80 ° of sweepback angle range, and costa end and blunt nosed edges of regions
Less than the 30% of Waverider half length, curve design for Waverider in streamlined impeller line；Low sweep angle region is also referred to as outer wing
Part, in the streamline both sides of big sweepback angular zone, the costa in low sweep angle region is straight line, angle of sweep for smooth connection
30°-70°.The optimum angle of sweep chosen less than big sweepback angular zone of angle of sweep size of low sweep angle region costa.Blunt nosed area
The distance of domain costa outermost end to axis of symmetry is less than the 40% of Waverider half length.
Fig. 4 gives the design diagram of three subregions, and circular arc AB is the shock wave outlet molded line of the design in blunt nosed region,
Central angle θ1, curve BC is the shock wave outlet molded line of big sweepback angular zone, and straight line CD is the shock wave outlet molded line in little sweepback region,
Slope inclination angle is θ2.
This pair of sweepback Waverider is kept in the high lift-drag ratio characteristic of hypersonic state.Using Fluid Mechanics Computation
(CFD) method carries out verifying and calculates, and Fig. 5 is that during Ma6, double sweepback Waverider lower surface isobars are distributed it can be seen that shock wave adheres to
In lower surface, limit leakage from lower surface to upper surface for the flowing, 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-drag ratio L/D with angle of attack change it can be seen that with outer wing part
The reduction at angle of sweep, the lift-drag ratio of Waverider has and is significantly lifted very much.
Double sweepback Waveriders improve longitudinal stability, and Fig. 7 (left) gives given inboard wing portion angle of sweep and is 70 °, changes
When becoming outboard wing sweep (70-30 °), moment C under hypersonic statemWith the change 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
To judge the static-stability characteristic of aircraft to pressure heart position with the change of the angle of attack.Fig. 7 (right) gives Center of Pressure Pr Ct with attacking
The change curve at angle, in such cases when outboard wing sweep is less than 60 °, increases with the angle of attack and moves behind pressure heart position, be subject in the angle of attack
Restoring moment can be produced it is ensured that Longitudinal static stability under flying condition after changing to disturbance.And outboard wing sweep is relatively
When big, Center of Pressure moves forward, static stability it cannot be guaranteed that.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (10)
1. a kind of pair of sweepback layout Waverider it is characterised in that：The upper surface of described Waverider is followed the trail of for free stream interface
The plane arriving, lower surface is the curved surface with rider performance, and this curved surface is by blunt nosed region, big sweepback angular zone and low sweep angle
Region is described；Wherein, the streamlined impeller curved surface during blunt nosed region is designed for Waverider, Blunt leading edge line is at axis of symmetry
The rate of cutting is zero；Big sweepback angular zone is also referred to as inboard wing portion, in smoothing junction in the both sides in blunt nosed region, its outer mold surface by costa and
Curve forms, and costa is big sweepback straight line, 50 ° -80 ° of sweepback angle range, and between costa end and blunt nosed edges of regions
Distance be less than Waverider half length 30%, curve design for Waverider in streamlined impeller line；Low sweep angle region is also referred to as
For outer wing part, in smoothing junction in the streamline both 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 pair of sweepback layout according to claim 1 Waverider it is characterised in that：Blunt nosed region is led using cone and is taken advantage of
In ripple body method, streamlined impeller initial line is set as that horizontal linear obtains.
3. a kind of pair of sweepback layout according to claim 1 Waverider it is characterised in that：Blunt nosed region is bored using close
Set shock wave outlet molded line in method as circular arc, set streamlined impeller initial line and obtain as horizontal linear.
4. a kind of pair of sweepback layout according to claim 1 or 2 or 3 Waverider it is characterised in that：Low sweep angle region
Using setting shock wave outlet molded line in close cone method as straight line, set flow field in osculating plane as supersonic speed wedge shape flow field,
Set streamlined impeller initial line to obtain as horizontal linear.
5. a kind of pair of sweepback layout according to claim 4 Waverider it is characterised in that：The shock wave in low sweep angle region
The slope inclination angle of outlet molded line is less than the central angle that blunt nosed region shock wave exports molded line circular arc.
6. a kind of pair of sweepback layout according to claim 1 Waverider it is characterised in that：Big sweepback angular zone adopts close
The design of cone of tangents method obtains, and wherein setting shock wave outlet molded line is that connection blunt nosed region shock wave exports molded line and is designated as curve A and little
Sweepback angular zone shock wave exports the smoothed curve that molded line is designated as curve B, and the curvature of this smoothed curve is set as the curvature from curve A
Linearly it is reduced to the curvature of curve B；Set streamlined impeller initial line as horizontal linear.
7. a kind of pair of sweepback layout according to claim 6 Waverider it is characterised in that：Described smoothed curve adopts
B-spline method is expressed, to ensure the slickness of transitional region.
8. a kind of pair of sweepback layout according to claim 1 Waverider it is characterised in that：Low sweep angle region costa
The optimum angle of sweep chosen less than big sweepback angular zone of angle of sweep size.
9. a kind of pair of sweepback layout according to claim 8 Waverider it is characterised in that：Low sweep angle region costa
Angle of sweep size optimum be less than 60 °.
10. a kind of pair of sweepback layout according to claim 1 Waverider it is characterised in that：Blunt nosed region costa is
The distance of outer end to axis of symmetry is less than the 40% of Waverider half length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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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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| CN201610912726.1A CN106394874B (en) | 2016-10-19 | 2016-10-19 | A kind of Waverider of double sweepback layouts |
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| CN106394874B CN106394874B (en) | 2019-01-25 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107253521A (en) * | 2017-07-03 | 2017-10-17 | 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 in curve head with changeover portion closely |
| CN107298162A (en) * | 2017-07-03 | 2017-10-27 | 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 sharp apex with changeover portion closely |
| CN108502204A (en) * | 2018-04-03 | 2018-09-07 | 北京航空航天大学 | Hypersonic group of jib and cotter 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 |
| CN111688905A (en) * | 2020-06-10 | 2020-09-22 | 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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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107253521A (en) * | 2017-07-03 | 2017-10-17 | 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 in curve head with changeover portion closely |
| CN107298162A (en) * | 2017-07-03 | 2017-10-27 | 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 sharp apex with changeover portion closely |
| 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 |
| CN108502204A (en) * | 2018-04-03 | 2018-09-07 | 北京航空航天大学 | Hypersonic group of jib and cotter Waverider design method |
| 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 |
| CN111688905A (en) * | 2020-06-10 | 2020-09-22 | 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 |
| 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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