CN204937477U - The aerofoil profile of a kind of low-resistance, low pitching moment - Google Patents
The aerofoil profile of a kind of low-resistance, low pitching moment Download PDFInfo
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- CN204937477U CN204937477U CN201520328713.0U CN201520328713U CN204937477U CN 204937477 U CN204937477 U CN 204937477U CN 201520328713 U CN201520328713 U CN 201520328713U CN 204937477 U CN204937477 U CN 204937477U
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Abstract
The utility model discloses the aerofoil profile of a kind of low-resistance, low pitching moment, it comprises aerofoil profile leading edge, aerofoil profile maximum ga(u)ge position and airfoil trailing edge, aerofoil profile maximum ga(u)ge position is mobile 2% chord length backward, aerofoil profile leading edge place camber curvature increases by 1% chord length, airfoil trailing edge camber curvature is made to reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, make zero lift moment absolute coefficient within 0.01.This aerofoil profile makes aerofoil profile meet minimum drag coefficient little, the zero lift moment coefficient requirement that as far as possible relaxes of little, At High Angle of Attack stalling characteristic as far as possible as far as possible, and then the drag coefficient of whole aerofoil profile is reduced, increases 1ift-drag ratio, the cruise efficiency of raising aerofoil profile.
Description
Technical field
The utility model relates to a kind of Aerodynamic Configuration of Aireraft structure, particularly relates to the aerofoil profile of a kind of low-resistance, low pitching moment.
Background technology
The aerodynamic characteristic of wing is directly connected to aircraft cruise performance and stalling characteristics, and the aerodynamic characteristic of aerofoil profile directly affects the aerodynamic characteristic of wing.Therefore, for pursuing the aircraft of cruise performance and stalling characteristics, the minimum drag coefficient of aerofoil profile, zero lift moment coefficient, At High Angle of Attack aerodynamic characteristic are the factors paid close attention to of Airfoil Optimization.
Therefore aircraft designer need according to flight, boat time, the aspect of wing, the stalling characteristics of aircraft, the aerofoil profile designed require minimum drag coefficient as far as possible little, zero lift moment coefficient as far as possible little, At High Angle of Attack stalling characteristic relax as far as possible.
Utility model content
The utility model technical issues that need to address are to provide the aerofoil profile of a kind of low-resistance, low pitching moment.
For solving technical matters of the present utility model, the technical solution adopted in the utility model is:
The aerofoil profile of a kind of low-resistance, low pitching moment, this aerofoil profile is NACA five digit number aerofoil profile, it comprises aerofoil profile leading edge, aerofoil profile maximum ga(u)ge position and airfoil trailing edge, aerofoil profile maximum ga(u)ge position is mobile 2% chord length backward, aerofoil profile leading edge place camber curvature increases by 1% chord length, make airfoil trailing edge camber curvature reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, make zero lift moment absolute coefficient within 0.01.
The beneficial effects of the utility model: in order to increase the stalling incidence of aerofoil profile, aerofoil profile leading edge place camber suitably increases, in order to control the zero lift moment coefficient of aerofoil profile, while aerofoil profile leading edge camber increases, 18% chord length is moved behind maximum camber position, make camber curvature near airfoil trailing edge reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, reach restriction zero lift moment absolute coefficient within 0.01; Aerofoil profile maximum ga(u)ge moves 2% chord length behind position, can increase the suitable nip territory of whole aerofoil, reduces the inverse nip territory of aerofoil, and then the drag coefficient of whole aerofoil profile is reduced, and increases 1ift-drag ratio, improves the cruise efficiency of aerofoil profile.
Accompanying drawing explanation
Fig. 1 is structure diagram of the present utility model.
Fig. 2 is low-resistance of the present utility model, the aerofoil camber of low pitching moment distributes and thickness distribution figure.
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.
Shown in Fig. 1 and Fig. 2, the aerofoil profile of a kind of low-resistance of the present utility model, low pitching moment, this aerofoil profile is NACA five digit number aerofoil profile, it comprises aerofoil profile leading edge 1, aerofoil profile maximum ga(u)ge position 2 and airfoil trailing edge 3, aerofoil profile maximum ga(u)ge position 2 is mobile 2% chord length backward, and aerofoil profile leading edge 1 place camber curvature increases by 1% chord length, makes airfoil trailing edge 3 camber curvature reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, make zero lift moment absolute coefficient within 0.01.
Be directed to the designing airfoil of low-resistance, low pitching moment, large stalling incidence, be mainly divided into aerofoil profile leading edge 1 in Fig. 1, aerofoil profile maximum ga(u)ge position 2 and airfoil trailing edge 3 three regions to be optimized design aerofoil profile.
(1) in order to reduce the minimum drag coefficient of aerofoil profile, aerofoil profile maximum ga(u)ge position 2 is mobile 2% chord length backward, if Fig. 2 aerofoil profile maximum ga(u)ge change in location is to 6 places, can reduce the region of aerofoil profile adverse pressure gradient, reaches the effect reducing resistance;
(2) in order to increase the stalling incidence of aerofoil profile, aerofoil profile leading edge 1 place camber curvature increases by 1% chord length, and the aerofoil profile leading edge camber as Fig. 2 changes 4 places;
(3) in order to reduce zero lift moment coefficient, at airfoil trailing edge 3 place, profi1e mean line recurvation is designed, make camber curvature near airfoil trailing edge reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, in Fig. 2,5 places give airfoil trailing edge mean line recurvation mean line situation of change.
This aerofoil profile makes aerofoil profile meet minimum drag coefficient little, the zero lift moment coefficient requirement that as far as possible relaxes of little, At High Angle of Attack stalling characteristic as far as possible as far as possible, and then the drag coefficient of whole aerofoil profile is reduced, increases 1ift-drag ratio, the cruise efficiency of raising aerofoil profile.
Claims (1)
1. the aerofoil profile of a low-resistance, low pitching moment, it is characterized in that: this aerofoil profile is NACA five digit number aerofoil profile, it comprises aerofoil profile leading edge, aerofoil profile maximum ga(u)ge position and airfoil trailing edge, aerofoil profile maximum ga(u)ge position is mobile 2% chord length backward, aerofoil profile leading edge place camber curvature increases by 1% chord length, make airfoil trailing edge camber curvature reduce 1% chord length, and then make aerofoil profile recurvation 0.5% chord length, make zero lift moment absolute coefficient within 0.01.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520328713.0U CN204937477U (en) | 2015-05-21 | 2015-05-21 | The aerofoil profile of a kind of low-resistance, low pitching moment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520328713.0U CN204937477U (en) | 2015-05-21 | 2015-05-21 | The aerofoil profile of a kind of low-resistance, low pitching moment |
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| CN204937477U true CN204937477U (en) | 2016-01-06 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741924A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | A kind of high lift-drag ratio Low-torque characteristic 9% thickness rotor-blade airfoil under the conditions of full working scope |
| CN106741923A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 7% under the conditions of a kind of full working scope |
| CN106741925A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 12% under the conditions of a kind of full working scope |
| CN110386243A (en) * | 2019-07-22 | 2019-10-29 | 北京耐威科技股份有限公司 | A kind of low-speed unmanned aerial vehicle aerofoil profile of high lift-drag ratio |
| CN115593612A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心空天技术研究所（Cn） | Self-leveling anti-stall high-performance airfoil |
-
2015
- 2015-05-21 CN CN201520328713.0U patent/CN204937477U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741924A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | A kind of high lift-drag ratio Low-torque characteristic 9% thickness rotor-blade airfoil under the conditions of full working scope |
| CN106741923A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 7% under the conditions of a kind of full working scope |
| CN106741925A (en) * | 2016-11-20 | 2017-05-31 | 西北工业大学 | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 12% under the conditions of a kind of full working scope |
| CN110386243A (en) * | 2019-07-22 | 2019-10-29 | 北京耐威科技股份有限公司 | A kind of low-speed unmanned aerial vehicle aerofoil profile of high lift-drag ratio |
| CN110386243B (en) * | 2019-07-22 | 2024-04-16 | 北京耐威科技股份有限公司 | High lift-drag ratio low-speed unmanned wing type |
| CN115593612A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心空天技术研究所（Cn） | Self-leveling anti-stall high-performance airfoil |
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