CN214524368U

CN214524368U - Lower single-wing aircraft with low coverage coupling guide vane

Info

Publication number: CN214524368U
Application number: CN202023029584.5U
Authority: CN
Inventors: 刘毅
Original assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Current assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Priority date: 2020-12-16
Filing date: 2020-12-16
Publication date: 2021-10-29
Anticipated expiration: 2030-12-16

Abstract

The utility model discloses a lower single wing aircraft with low coverage coupling water conservancy diversion piece, including fuselage, wing with set up in just be located on the fuselage low coverage coupling water conservancy diversion piece of top before the wing root. The utility model discloses a lower single wing aircraft is through installing a water conservancy diversion piece additional on the fuselage of wing root front upper place for the wake vortex of water conservancy diversion piece is the airflow separation district injection high velocity air current of wing root, is showing and postpones wing root air current separation, makes the aircraft maximum lift coefficient obtain promoting, and the aircraft can adopt less wing area under the same condition, thereby has reduced aircraft weight, has reduced flight resistance, improves flight performance.

Description

Lower single-wing aircraft with low coverage coupling guide vane

Technical Field

The utility model belongs to the technical field of the aircraft, specifically speaking, the utility model relates to a lower single wing aircraft with low coverage coupling water conservancy diversion piece.

Background

The lower single-wing aircraft refers to an aircraft with the joint point of the wings and the fuselage at the lower part of the fuselage, and other combination modes comprise a middle single wing and an upper single wing, namely the wings and the fuselage are connected at the middle part and the upper part of the latter. The lower single wing layout is one of the common layout forms of civil aviation airliners and navigation fixed wing aircrafts, has the advantages of easy arrangement of undercarriage, low engine position, convenient maintenance, convenient arrangement of passenger cabins and the like, and has the defects that airflow separation is easy to occur at the joint of the wings and the fuselage, so that the aerodynamic drag is large, and the lower single wing layout is not suitable for aircrafts with specific purposes and the like.

The close-coupled duck wing is one of the mainstream advanced aerodynamic layout design technologies of fighters, and typical airplanes adopting the technology comprise JAS39 in Sweden, gust in France, Jian 10 in China and the like. The main mechanism of the close-range coupling canard is that the canard is arranged at a position close to the front upper part of the wing of the airplane, and strong wake vortexes are generated on the canard to form favorable interference with vortexes of the wing at the rear part, so that the lift force of the wing vortexes is enhanced, the lift force stall is delayed, and the performances of short-distance take-off and landing, large attack angle maneuverability and the like of the fighter are improved.

The joint of the wing and the fuselage of the lower single-wing aircraft is easy to generate an airflow separation area, and the problems of resistance increase, lift reduction and the like can occur unless a larger rectification transition section is designed. For small aircraft, the rear fuselage section is usually contracted to intensify the airflow separation, and the design of a larger rectifying transition section is not feasible, so that a larger wing area is required to make up for the deficiency of lift force, and the weight and the drag of the aircraft structure are increased. The close-range coupling canard wing technology is mainly used for fighters and cannot be directly used for lower single-wing transport airplanes.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a lower single-wing aircraft with low coverage coupling water conservancy diversion piece, the purpose improves flight performance.

In order to realize the purpose, the utility model discloses the technical scheme who takes does: the lower single-wing aircraft with the close-range coupling guide vane comprises an airframe, wings and the close-range coupling guide vane arranged on the airframe and positioned in front of and above the root of the wings.

The chord length C2 of the middle section of the close coupling guide vane is 0.15C 1-0.20C 1, and C1 is the chord length of the wing root.

The minimum GAP GAP between the close coupling guide vane and the airfoil of the wing is 0.09C 1-0.12C 1.

The overlapping amount O/L of the close coupling guide vane is 0.01C 1-0.03C 1.

The mounting angle theta of the close-coupled guide vane is a negative value, the specific magnitude of the close-coupled guide vane is determined by a numerical calculation method considering viscosity, and the condition that the normal force stall attack angle of the guide vane is just larger than the stall attack angle of the wing is met.

The utility model discloses a lower single wing aircraft is through installing a water conservancy diversion piece additional on the fuselage of wing root front upper place for the wake vortex of water conservancy diversion piece is the airflow separation district injection high velocity air current of wing root, is showing and postpones wing root air current separation, makes the aircraft maximum lift coefficient obtain promoting, and the aircraft can adopt less wing area under the same condition, thereby has reduced aircraft weight, has reduced flight resistance, improves flight performance.

Drawings

The description includes the following figures, the contents shown are respectively:

fig. 1 is a schematic structural view of a lower single-wing aircraft with close-coupled deflectors of the present invention;

fig. 2 is a schematic top view dimension view of a short-distance coupling guide vane;

fig. 3 is a schematic view of the cross-section a-a dimension of the near coupling guide vane;

FIG. 4 shows the variation (calculated value) of lift characteristics of a reference plane with attached deflectors;

labeled as: 1. a body; 2. an airfoil; 3. the guide vane is coupled in a short distance.

Detailed Description

The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.

As shown in fig. 1 to 3, the utility model provides a lower single wing aircraft with low coverage coupling guide vane, including fuselage, wing and set up on the fuselage and be located the low coverage coupling guide vane of wing root front upper place.

Specifically, as shown in fig. 1 to 3, the wings and the short-distance coupling guide vanes are arranged in a left-right symmetrical manner, the wings and the short-distance coupling guide vanes are fixedly connected to the fuselage, the wings and the short-distance coupling guide vanes extend out towards the outer side of the fuselage, the extension length of the short-distance coupling guide vanes is far smaller than that of the wings, and the short-distance coupling guide vanes are respectively positioned above and in front of the root of the wings on the same side. In the flying process of the airplane, the wake vortex of the near-coupled guide vane injects high-speed airflow into the airflow separation area at the root of the wing, so that the airflow separation at the root of the wing can be remarkably delayed, the maximum lift coefficient of the airplane is improved, and the airplane can adopt a smaller wing area under the same condition, thereby reducing the weight of the airplane, reducing the flying resistance and improving the flying performance.

The schematic shape diagrams of the short-distance coupling guide vane in the top view and the middle section are respectively shown in fig. 2 and fig. 3. All dimensions are given as relative values of the profile chord length C1 in the mid-profile or the profile chord length C2 in the near coupled guide vane.

As shown in fig. 2, in the top view, the height H of the short-distance coupling guide vane is 0.16C 1-0.18C 1, the root chord length Cr is 1.1C 2-1.3C 2, and the tip chord length Ct is 0.7C 2-0.9C 2.

As shown in fig. 3, a chord length C2 of the middle section of the near coupling guide vane is 0.15C 1-0.20C 1, a minimum GAP between the near coupling guide vane and the airfoil of the wing is 0.09C 1-0.12C 1, an overlap amount O/L of the near coupling guide vane is 0.01C 1-0.03C 1, an installation angle θ of the near coupling guide vane is a negative value, and a specific magnitude of the installation angle θ is determined by a numerical calculation method considering viscosity, so that a condition that a normal force stall attack angle of the guide vane is just larger than a stall attack angle of the wing is satisfied.

The profile shape of the close-range coupling guide vane is a wing profile with a camber, the relative thickness of the wing profile is 12% -15%, the trailing edge of the wing profile is thickened, so that a larger lift force and a stronger wake vortex can be obtained, and the wing profile is convenient to manufacture.

The influence of the near-distance coupling guide vane on the aerodynamic characteristics of a certain single-wing navigation aircraft is researched by adopting a numerical calculation method, and the result is shown in figure 4. As can be seen from fig. 4, the aircraft, after being provided with the guide vanes, has no obvious influence on the lift characteristic in the range of an attack angle alpha less than or equal to 6 degrees, the lift coefficient gradually increases after the angle alpha is greater than 6 degrees, the maximum lift coefficient increases by 0.2, and the increase proportion is 15 percent. The benchmark airplane has airflow separation area in the wing root area, and the wake vortex produced by the guide vane passes through the separation area, so that the separation is obviously improved.

The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.

Claims

1. The utility model provides a lower single wing aircraft with low coverage coupling guide vane, includes fuselage and wing, its characterized in that: the near-distance coupling guide vane is arranged on the machine body and positioned in front of and above the wing root;

2. The lower monowing aircraft with close-coupled flow deflector of claim 1, wherein: the minimum GAP GAP between the close coupling guide vane and the airfoil of the wing is 0.09C 1-0.12C 1.

3. The lower monowing aircraft with close-coupled deflectors of claim 1 or 2, wherein: the overlapping amount O/L of the close coupling guide vane is 0.01C 1-0.03C 1.

4. The lower monowing aircraft with close-coupled deflectors of claim 1 or 2, wherein: and the mounting angle theta of the close-distance coupling guide vane is a negative value.