CN206155818U - Rider body of whirlpool effect lift -rising - Google Patents
Rider body of whirlpool effect lift -rising Download PDFInfo
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- CN206155818U CN206155818U CN201621139702.9U CN201621139702U CN206155818U CN 206155818 U CN206155818 U CN 206155818U CN 201621139702 U CN201621139702 U CN 201621139702U CN 206155818 U CN206155818 U CN 206155818U
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Abstract
The utility model provides a rider body of whirlpool effect lift -rising, the upper surface of the rider body follow the trail of the plane that obtains for free stream interface, the lower surface has the curved surface of rider performance, this curved surface passes through the fuselage, the whirlpool generates the device and quick -witted wing part describes, wherein, the fuselage is the circular conical surface, and its bottom surface centre of a circle angle range is less than 90, the whirlpool generates the device smooth connection to comprise leading edge line and edge line in circular conical surface fuselage both sides, its outer profile, is the leading edge line big sweepback straight line, sweepback angle range 50 75, and the leading edge line terminal with the fuselage symmetry axis between the distance to be less than half exhibition of the rider body long by 40%, the edge line is the streamline pursuit line of the rider body in designing, the wing smooth connection generates the streamline both sides of device in the whirlpool, the leading edge line of wing is a straight line, and its sweep angle is lighter than the sweep angle that the whirlpool generated the device.
Description
Technical field
The invention belongs to the design of hypersonic aircraft design field, particularly Waverider aerodynamic arrangement.
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 utilizes this characteristic
Representative configuration.High-pressure pneumatic is segmented in the prevention flowing leakage of aircraft lower surface by Waverider by adhering to shock wave, is effectively broken through
The liter resistance barrier of hypersonic aircraft, with very high lift-drag ratio.Through the development of decades, list of the Waverider from early stage
One configuration gradually develops into the complex configuration with different characteristics, and the proposition of method is especially bored closely, can be swashed by given
Ripple outlet molded line carries out Waverider design, the Waverider profile with more characteristics.The high lift-drag ratio characteristic of Waverider profile is
The development of hypersonic aircraft provides good thinking.
At present hypersonic fighter plane is also rested among imagination, but is developed extremely urgent.Fighter plane to mobility and
High-lift has very high requirement, and in hydrodynamics, most one of the powerful for increasing lift is exactly whirlpool, and vortex lift characteristic is earliest
The slender wing of big sweepback is found in, air-flow separates to form whirlpool in Low Angle Of Attack from the leading edge of a wing, and highly stable.With attacking
Angle increases, and whirlpool intensity constantly strengthens, and generates very big vortex lift.Early 1970s occur in that the pneumatic cloth of strake wing
Office, it be in the front of the wing edge strip that plus elongated, except the lift-rising of edge strip whirlpool, can also be using edge strip and rear wing
Interference, therefore the lift of full machine can be increased substantially in High Angle of Attack, and reduce resistance.However, this whirlpool effect lift-rising dress
The application put in the hypersonic stage is also more rare.
The content of the invention
The present invention technology solve problem be：A kind of Waverider of whirlpool effect lift-rising is provided, by whirlpool effect, Waverider is made
During the increase angle of attack there is lift to increase effect, be that high motor-driven hypersonic fighter plane design lays the foundation.
The present invention technical solution be：A kind of Waverider of whirlpool effect lift-rising, the upper surface of described Waverider is
Free stream interface follows the trail of the plane for obtaining, and lower surface has the curved surface of rider performance, and the curved surface passes through fuselage, whirlpool generating means and machine
Alar part is described；Wherein, fuselage is taper seat, and its bottom surface center of circle angle range is less than 90 °；Whirlpool generating means it is in smoothing junction in
Taper seat fuselage both sides, its outer mold surface is big sweepback straight line into, costa by costa and group of edge lines, 50 ° of sweepback angle range-
75 °, and the distance between costa end and fuselage axis of symmetry, less than the 40% of the length of Waverider half, edge line sets for Waverider
Streamlined impeller line in meter；Wing is in smoothing junction, and in the streamline both sides of whirlpool generating means, the costa of wing is straight line, its
Angle of sweep of the angle of sweep less than whirlpool generating means.
Seamlessly transit between the costa end of whirlpool generating means and leading edge of a wing line.
The angle of sweep span of wing is more than 30 °.
The summit of fuselage taper seat is the stationary point of Waverider.
The present invention has the beneficial effect that compared with prior art：
(1) increase with the angle of attack, the lift of whirlpool effect Waverider has the effect of non-linear increase, when the angle of attack is 10 °, rise
Power increases up to 10% or so
(2) similar to strake wing, whirlpool effect is enhanced by the favourable interference of whirlpool generating means and wing section, while can
To reach the effect of drag reduction
(3) in order to strengthen the effect of whirlpool effect, whirlpool generating means leading edge sweep must be larger, is typically chosen more than 50 °, but
Generally less than 75 °, the generation of otherwise Waverider is had any problem；The angle of sweep of wing section is less than whirlpool generating means part, otherwise
There is no the interference effect in (2).But should not be too small, when the angle of sweep of wing section is less than 30 °, aircraft volume is too little, real
It is not high with being worth.
Description of the drawings
Fig. 1 is the outline drawing of whirlpool effect lift-rising Waverider；
Fig. 2 selects big logotype for the curved surface of whirlpool effect Waverider fuselage sections；
Fig. 3 is non-linear lift-rising of the profile lift of the present invention with the angle of attack；
Upper surface pressure distribution contrast when Fig. 4 is the big angle of attack.
Specific embodiment
Design principle of the present invention：Increase big angle of sweep leading edge profile on the inside of Waverider profile, similar to strake wing big
Whirlpool is produced during the angle of attack increases lift.
Figure gives the outline drawing of whirlpool effect Waverider.The upper surface of Waverider is that free stream interface follows the trail of the plane for obtaining,
Lower surface has the curved surface of rider performance, and the curved surface is described by fuselage, whirlpool generating means and wing section；A, B, C point
Not Dui Ying fuselage sections, whirlpool generating means and wing section, whirlpool generating means smooth connection in taper seat fuselage both sides, its external form
Face is by costa l1With edge line l2Composition, costa be big sweepback straight line, 50 ° -75 ° of sweepback angle range, and costa end with
The distance between fuselage axis of symmetry less than the 40% of the length of Waverider half, edge line design for Waverider in streamlined impeller line；
Wing smooth connection is in the streamline both sides of whirlpool generating means, the costa l of wing3For straight line, its angle of sweep is given birth to less than whirlpool
Into the angle of sweep of device.Seamlessly transit between the costa end of whirlpool generating means and leading edge of a wing line.After the generating means of whirlpool
Sweep angle is larger, can haul out leading vortex, reduces the pressure of upper surface.Figure is fuselage design diagram, and fuselage is one section of conic
Face, bottom surface central angle is θ, and scope is less than 90 °, and the summit of fuselage taper seat is the stationary point of Waverider.
Optimum, on the basis of the generating means angle of sweep of light rain whirlpool, span is more than 30 ° at the angle of sweep of wing.
Using CFD technology evaluation aeroperformances, figure gives increases whirlpool effect Waverider lift coefficient C with the angle of attackLWith attacking
The change of angle α, it can be seen that compared with the profile without whirlpool generating means, the lift coefficient of whirlpool effect Waverider has substantially
Non-linear lift-rising effect.
Whirlpool generating means and rear wing section generate favourable interference, and in the big angle of attack state effect in whirlpool is enhanced, scheme to
Big angle of attack state upper surface pressure line profiles versus are gone out, the whirlpool that whirlpool generating means are hauled out reduces the pressure of upper surface, and one
Directly affect to rear body region.
This specification unspecified part belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. a kind of Waverider of whirlpool effect lift-rising, it is characterised in that：The upper surface of described Waverider is followed the trail of for free stream interface
The plane for arriving, lower surface has the curved surface of rider performance, and the curved surface is retouched by fuselage, whirlpool generating means and wing section
State；Wherein, fuselage is taper seat, and its bottom surface center of circle angle range is less than 90 °；Whirlpool generating means smooth connection is in taper seat fuselage two
Side, its outer mold surface is by costa with group of edge lines into costa is big sweepback straight line, 50 ° -75 ° of sweepback angle range, and costa
, less than the 40% of the length of Waverider half, the streamline during edge line is designed for Waverider is chased after for the distance between end and fuselage axis of symmetry
Track line；Wing is in smoothing junction in the streamline both sides of whirlpool generating means, and the costa of wing is straight line, and its angle of sweep is less than whirlpool
The angle of sweep of generating means.
2. the Waverider of effect lift-rising in whirlpool according to claim 1, it is characterised in that：The costa end of whirlpool generating means
Seamlessly transit between leading edge of a wing line.
3. the Waverider of effect lift-rising in whirlpool according to claim 1, it is characterised in that：The angle of sweep span of wing is big
In 30 °.
4. the Waverider of effect lift-rising in whirlpool according to claim 1, it is characterised in that：The summit of fuselage taper seat is rider
The stationary point of body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621139702.9U CN206155818U (en) | 2016-10-19 | 2016-10-19 | Rider body of whirlpool effect lift -rising |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621139702.9U CN206155818U (en) | 2016-10-19 | 2016-10-19 | Rider body of whirlpool effect lift -rising |
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| Publication Number | Publication Date |
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| CN206155818U true CN206155818U (en) | 2017-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621139702.9U Active CN206155818U (en) | 2016-10-19 | 2016-10-19 | Rider body of whirlpool effect lift -rising |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394874A (en) * | 2016-10-19 | 2017-02-15 | 中国航天空气动力技术研究院 | Wave rider of dual sweepback layout |
| 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 |
| CN112606996A (en) * | 2020-12-30 | 2021-04-06 | 中国航天空气动力技术研究院 | Wave rider structure |
-
2016
- 2016-10-19 CN CN201621139702.9U patent/CN206155818U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394874A (en) * | 2016-10-19 | 2017-02-15 | 中国航天空气动力技术研究院 | Wave rider of dual sweepback layout |
| CN106394874B (en) * | 2016-10-19 | 2019-01-25 | 中国航天空气动力技术研究院 | A kind of Waverider of double sweepback layouts |
| 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 |
| CN112606996A (en) * | 2020-12-30 | 2021-04-06 | 中国航天空气动力技术研究院 | Wave rider structure |
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