CN204937472U - A kind of aerofoil profile being directed to dopey - Google Patents
A kind of aerofoil profile being directed to dopey Download PDFInfo
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- CN204937472U CN204937472U CN201520329304.2U CN201520329304U CN204937472U CN 204937472 U CN204937472 U CN 204937472U CN 201520329304 U CN201520329304 U CN 201520329304U CN 204937472 U CN204937472 U CN 204937472U
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Abstract
The utility model discloses a kind of aerofoil profile being directed to dopey, comprise leading-edge radius of airfoil, aerofoil profile leading edge portion, airfoil trailing edge upper surface and aerofoil profile maximum camber position, leading-edge radius of airfoil place to aerofoil profile exterior region office increases by 8% relative to base profile NACA63 camber, airfoil trailing edge upper surface increases by 0.5 ~ 1% relative to base profile NACA63 curvature, airfoil trailing edge upper surface Curvature varying relaxes relatively, and aerofoil profile maximum camber position to move forward 4.7% chord length relative to base profile NACA63.This aerofoil profile meets the requirement of high lift-drag ratio, high coefficient of lift combined, stalling characteristics mitigation.
Description
Technical field
The utility model relates to a kind of Aerodynamic Configuration of Aireraft structure, particularly relates to a kind of aerofoil profile being directed to dopey.
Background technology
For elementary basic schoolaeroplane or slow speed trick class aircraft, while economy given prominence to by aircraft, aircraft will do complicated motor-driven and large overload, consider from aircraft ability, require that aircraft has larger lift coefficient, from security consideration, plane wing surfaces stalling characteristics must relax.The stalling characteristics of aerofoil surface, maximum lift coefficient and aerofoil profile have much relations.Aerofoil profile maximum lift coefficient is little, affects the motor-driven overload capacity of aircraft.The stalling characteristics of aerofoil profile are poor, affect the safety of aircraft.
Therefore aircraft designer need according to elementary basic schoolaeroplane flight, boat time, overload size, size that the wing carries, aircraft stalling characteristics, select suitable standard aerofoil profile or utilize optimal design means to design the aerofoil profile met the demands, this aerofoil profile needs to have high lift-drag ratio, high coefficient of lift combined, stalling characteristics mitigation.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Utility model content
The utility model technical issues that need to address are to provide a kind of aerofoil profile being directed to dopey.
For solving technical matters of the present utility model, the technical solution adopted in the utility model is:
A kind of aerofoil profile being directed to dopey, it comprises leading-edge radius of airfoil, aerofoil profile leading edge portion, airfoil trailing edge upper surface and aerofoil profile maximum camber position, leading-edge radius of airfoil place to aerofoil profile exterior region office increases by 8% relative to base profile NACA63 camber, airfoil trailing edge upper surface increases by 0.5 ~ 1% relative to base profile NACA63 curvature, airfoil trailing edge upper surface Curvature varying relaxes relatively, and aerofoil profile maximum camber position to move forward 4.7% chord length relative to base profile NACA63.
The beneficial effects of the utility model: in order to reduce the adverse pressure gradient of aerofoil profile upper surface, reduce leading-edge suction peak value, increase the maximum stalling incidence of aerofoil profile, when ensureing that leading-edge radius of airfoil is substantially constant, leading-edge radius of airfoil place to aerofoil profile exterior region office increases by 8% relative to base profile camber, simultaneously aerofoil profile maximum camber position moves forward 4.7% chord length, when ensureing that leading edge thickness distribution is substantially constant, airfoil trailing edge upper surface increases by 0.5 ~ 1% relative to base profile curvature, change the thickness distribution at airfoil trailing edge place, change is relaxed more, this aerofoil profile meets high lift-drag ratio, high coefficient of lift combined, the requirement that stalling characteristics relax.
Accompanying drawing explanation
Fig. 1 is structure diagram of the present utility model.
Fig. 2 is airfoil trailing edge thickness distribution variation diagram (NACA63 is base profile, and B120-11 are designing airfoil).
Fig. 3 is aerofoil profile leading edge camber changes in distribution figure (NACA63 is base profile, and B120-11 are designing airfoil).
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.
A kind of aerofoil profile being directed to dopey of the present utility model, it comprises leading-edge radius of airfoil 1, aerofoil profile leading edge portion 2, airfoil trailing edge upper surface 3 and aerofoil profile maximum camber position 4, leading-edge radius of airfoil 1 place to aerofoil profile leading edge portion 2 place increases by 8% relative to base profile NACA63 camber, airfoil trailing edge upper surface 3 increases by 0.5 ~ 1% relative to base profile NACA63 curvature, airfoil trailing edge upper surface 3 Curvature varying relaxes relatively, and aerofoil profile maximum camber position 4 to move forward 4.7% chord length relative to base profile NACA63.
Shown in Fig. 1, in Airfoil Optimization process, be mainly divided into leading-edge radius of airfoil 1, aerofoil profile leading edge portion 2, airfoil trailing edge upper surface 3, these regions, aerofoil profile maximum camber position 4 are optimized design.
(1) be directed to the aircraft of outstanding air maneuver and aircraft stall characteristic, the airfoil stall angle of attack is large, stalling characteristics relax, in order to the maximum stalling incidence of outstanding aerofoil profile, leading-edge radius of airfoil 1 place to aerofoil profile leading edge portion 2 place increases by 8% relative to base profile camber.
(2) in order to the stalling characteristic of outstanding aerofoil profile relaxes, airfoil trailing edge upper surface 3 increases by 0.5 ~ 1% relative to base profile curvature, airfoil trailing edge upper surface 3 Curvature varying relaxes relatively, gives the change of profile thickness distribution in Fig. 2, and the change of airfoil trailing edge thickness 5 place relaxes more.
(3) in order to the adverse pressure gradient of less upper surface, reduce leading-edge suction peak value, make the resistant to separation ability of aerofoil surface stronger, make aerofoil profile maximum camber position move forward to 4.7% chord positions, aerofoil profile leading edge camber 6 is as Fig. 3.
Claims (1)
1. one kind is directed to the aerofoil profile of dopey, it is characterized in that: it comprises leading-edge radius of airfoil, aerofoil profile leading edge portion, airfoil trailing edge upper surface and aerofoil profile maximum camber position, leading-edge radius of airfoil place to aerofoil profile exterior region office increases by 8% relative to base profile NACA63 camber, airfoil trailing edge upper surface increases by 0.5 ~ 1% relative to base profile NACA63 curvature, airfoil trailing edge upper surface Curvature varying relaxes relatively, and aerofoil profile maximum camber position to move forward 4.7% chord length relative to base profile NACA63.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520329304.2U CN204937472U (en) | 2015-05-21 | 2015-05-21 | A kind of aerofoil profile being directed to dopey |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520329304.2U CN204937472U (en) | 2015-05-21 | 2015-05-21 | A kind of aerofoil profile being directed to dopey |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204937472U true CN204937472U (en) | 2016-01-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520329304.2U Active CN204937472U (en) | 2015-05-21 | 2015-05-21 | A kind of aerofoil profile being directed to dopey |
Country Status (1)
| Country | Link |
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| CN (1) | CN204937472U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828875A (en) * | 2016-12-27 | 2017-06-13 | 西北工业大学 | A kind of laminar flow airfoil that characteristic of climbing is laid particular stress on suitable for general purpose vehicle |
| CN106828874A (en) * | 2016-12-27 | 2017-06-13 | 西北工业大学 | A kind of laminar flow airfoil that stalling characteristics are laid particular stress on suitable for general purpose vehicle |
-
2015
- 2015-05-21 CN CN201520329304.2U patent/CN204937472U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828875A (en) * | 2016-12-27 | 2017-06-13 | 西北工业大学 | A kind of laminar flow airfoil that characteristic of climbing is laid particular stress on suitable for general purpose vehicle |
| CN106828874A (en) * | 2016-12-27 | 2017-06-13 | 西北工业大学 | A kind of laminar flow airfoil that stalling characteristics are laid particular stress on suitable for general purpose vehicle |
| CN106828875B (en) * | 2016-12-27 | 2018-11-16 | 西北工业大学 | A kind of laminar flow airfoil laying particular stress on characteristic of climbing suitable for general purpose vehicle |
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