CN203593160U

CN203593160U - Wing structure

Info

Publication number: CN203593160U
Application number: CN201320823086.9U
Authority: CN
Inventors: 刘庆萍; 任露泉; 廖庚华; 陈新
Original assignee: Jilin University
Current assignee: Jilin University
Priority date: 2013-12-13
Filing date: 2013-12-13
Publication date: 2014-05-14
Anticipated expiration: 2023-12-13

Abstract

The utility model discloses an airfoil structure, which is continuously formed by airfoil sections, and the airfoil sections are respectively 0%, 20%, 40%, 60%, 80%, and 100% spanwise from the root of the wing. length; the ratio of the span length to the chord length is 5.50 to 7.24; the leading edge of the wing is a high-order curve approximately parabolic: the maximum relative camber of each airfoil section is 7.5%, which is located at 17-33% of the chord length; each wing The maximum relative thickness of the airfoil profile is 13.1%, which is located at 11-24% of the chord length; along the span direction, the camber and thickness of the airfoil profile first increase and then decrease. Compared with the NACA 4-digit airfoil with similar parameters, the utility model has a larger low-speed lift coefficient, a smaller drag coefficient, and a larger stall angle; under the same flight parameters, the utility model has lower flight noise; the utility model When the angle of attack is 25°, it still has a large lift coefficient, and after exceeding 25°, the lift coefficient decreases slowly.

Description

A kind of wing structure

Technical field

The utility model relates to a kind of wing structure of aircraft.

Background technology

The types such as aerodone, hydroairplane, prototype, unmanned plane, because power is less or unpowered, need wing to have higher lift coefficient, are convenient to take off.Cruising phase, in order to strengthen voyage, requires wing to have higher lift coefficient and lower drag coefficient.Unmanned plane usually needs to carry out scoutings and waits special duty, enters and scouts behind region, often needs to close power flide and flies, and this just requires wing to have higher lift coefficient to possess lower flight noise simultaneously.

Prior art, is usually used NACA4 figure place series aerofoil profile, and this series aerofoil profile is applicable to compared with the propeller aeroplane of low velocity flight.

But this series aerofoil profile aerodynamic performance is desirable not to the utmost, can not meet some special requirement.Especially stall angle and flight noise aspect.

Take more typical NACA2412 aerofoil profile as example, this aerofoil profile reaches 20 while spending at the angle of attack, and lift coefficient reaches maxim, and between 20 degree-30 degree, lift coefficient slow decreasing, reaches after 30 degree, and lift coefficient sharply declines, and enters stall condition, as shown in Figure 1.

Prototype, unmanned plane and hydroairplane owing to usually there is no sufficient length take off distance, need to take off in short range, need the large angle of attack to take off and obtain enough large lift coefficient on one side.

Summary of the invention

The purpose of this utility model is to provide a kind of wing structure of aircraft, and the utility model is applicable to aerodone, hydroairplane, prototype, the scounting aeroplane wing that speed is lower.The utility model is 30 while spending at the angle of attack, still has larger lift coefficient, and exceedes after 30 degree, and lift coefficient suppression ratio is slower.

The utility model is to be made up of continuously aerofoil profile,

Described aerofoil profile is respectively apart from wing root 0%, 20%, 40%, 60%, and 80%, 100% exhibition is to length.

Span ratio (aspect ratio) long and chord length is 5.50～7.24.

Described chord length refers to standard mean chord SMC=S/b, and wherein S is blade area, and b is span length.

Nose of wing is approximate Parabolic high order curve:

2x/b=-2.3ξ5+3.752ξ4-1.942ξ3+0.192ξ2+0.077ξ-0.003；

Wherein: 2x/b is tangential ratio,

ξ=2y/b for exhibition to than,

X is tangential coordinate,

Y is for exhibition is to coordinate.

Aerofoil profile feature is that leading-edge radius is larger, and camber is larger relatively, and relative thickness is less.

Each aerofoil profile maximal phase is 7.5% to camber, is positioned at the 17-33% place of chord length;

Each aerofoil profile maximum relative thickness is 13.1%, is positioned at the 11-24% place of chord length.

Edge exhibition is all the trend of first increases and then decreases to aerofoil profile camber and thickness.

The beneficial effects of the utility model:

1, the NACA4 figure place aerofoil profile that reduced parameter is approximate, low speed lift coefficient is larger, and drag coefficient is less, has larger angle of stall(ing).

2,, in the situation that flight parameter is identical, the utility model flight noise is lower.

3, the utility model, at the angle of attack when exceeding 25 °, still has larger lift coefficient, and exceedes after 25 °, and lift coefficient suppression ratio is slower.

4, the utility model is applicable to aerodone, hydroairplane, prototype, the scounting aeroplane wing that speed is lower.

Accompanying drawing explanation

Fig. 1 is that the utility model aerofoil profile and NACA2412 wing section lift coefficient and the angle of attack are related to correlation curve figure.

Fig. 2 is the utility model aerofoil profile and NACA2412 aerofoil profile aerodynamics noise and flow velocity relation correlation curve figure.

Fig. 3 be the utility model extend to aerofoil profile figure.

Fig. 4 is the utility model airfoil geometry structure and parameters schematic diagram.

The specific embodiment

The utility model is to be made up of continuously aerofoil profile,

Described aerofoil profile is respectively apart from wing root 0%, 20%, 40%, 60%, and 80%, 100% exhibition is to length.Provide the coordinate of above aerofoil profile with coordinate method, as shown in Figure 3 and Figure 4, profile thickness reduces to end (100%) gradually from root (0%), and aerofoil camber also reduces gradually, and aerofoil profile width root and end are slightly little, and aerofoil profile middle part is slightly large.

Span ratio (aspect ratio) long and chord length is 5.50～7.24;

Nose of wing is approximate Parabolic high order curve:

2x/b=-2.3ξ5+3.752ξ4-1.942ξ3+0.192ξ2+0.077ξ-0.003。

Wherein: 2x/b is tangential ratio, ξ=2y/b for exhibition to than, x is tangential coordinate, y for exhibition to coordinate.

Maximum relative thickness is 13.1%, is positioned at the 11-24% place of chord length.

As shown in Figure 1, upper curve is the utility model aerofoil profile, lower curve is NACA2412 aerofoil profile, can find out with the variation of the angle of attack from lift curve, the utility model aerofoil profile is that within the scope of 5-30 °, lift coefficient, higher than NACA2412 aerofoil profile, and exceedes after 25 ° at the angle of attack at the angle of attack, still there is larger lift coefficient, the NACA2412 aerofoil profile angle of attack exceedes after 25 °, and lift coefficient sharply declines, and occurs stall phenomenon.

As shown in Figure 2, lower curve is the utility model aerofoil profile, upper curve is NACA2412 aerofoil profile, be below 20m/s at flow velocity, two kinds of aerofoil profile aerodynamics noises are more approaching, when flow velocity exceedes after 20m/s, the utility model aerofoil profile noise starts the aerofoil profile lower than NACA2412, and along with flow velocity increases, the utility model aerofoil profile and NACA2412 aerofoil profile noise gap are increasing, and the utility model aerofoil profile noise reduction is more remarkable under high speed.

0%, 20%, 40%, 60%, 80%, 100% exhibition to the aerofoil profile coordinate of length respectively as shown in table 1, table 2, table 3, table 4, table 5 and table 6:

Table 1 00% aerofoil profile coordinate

Table 2 20% aerofoil profile coordinate

Table 3 40% aerofoil profile coordinate

Table 4 60% aerofoil profile coordinate

Table 5 80% aerofoil profile coordinate

Table 6 100% aerofoil profile coordinate

Claims

1. A wing structure is characterized in that: it is formed continuously by airfoil section,

The airfoil section is respectively 0%, 20%, 40%, 60%, 80%, and 100% span length from the root of the wing;

The ratio of wingspan length to chord length is 5.50～7.24;

The chord length refers to the standard average chord length SMC=S/b, wherein: S is the wing area, and b is the span length;

The leading edge of the wing is a high degree curve approximately parabolic:

2x/b=-2.3ξ5+3.752ξ4-1.942ξ3+0.192ξ2+0.077ξ-0.003;

Where: 2x/b is the chord ratio,

ξ=2y/b is the span ratio,

x is the chordal coordinate,

y is the spanwise coordinate;

The leading edge of the airfoil has a larger radius, larger relative curvature, and smaller relative thickness;

The maximum relative camber of each airfoil section is 7.5%, located at 17-33% of the chord length;

The maximum relative thickness of each airfoil section is 13.1%, located at 11-24% of the chord length.