Flying vehicle wing tip

FIELD: aeronautical engineering; various flying vehicles.

SUBSTANCE: proposed tip has end plate and is provided with additional swept aerodynamic surface of low aspect ratio with sharp leading edge mounted on the outside of end plate. Trailing edge of additional aerodynamic surface is combined with trailing edge of end plate. Nose is located on leading edge of end plate below level of trailing edge; sweep ranges from 60° to 85°.

EFFECT: enhanced aerodynamic efficiency at high subsonic speeds.

15 dwg

 

The invention relates to the field of aviation technology and can be used on bearing surfaces of aircraft for various purposes.

Famous wing tip of the aircraft, having an end plate (U.S. patent No. 4245804, NCI 244-91, 1977).

However, existing wingtips with vertical end plates, including having the camber angle γ≠0 (the angle between the vertical and the plane of the end washers), not in full use components of the vectors of the local flow velocities of spatial wrap the end of the wing. Physics work vertical end plate based on their interaction with the horizontal components of the bevels of the stream and at an angle of collapse γ>0 vertical bevels flow only partially involved. Therefore, the aerodynamic efficiency is known wingtips insufficient.

An object of the invention is to increase the aerodynamic efficiency of the wing tip end with the puck.

The goal of the project is achieved by the fact that the wing tip of the aircraft, having an end plate provided with an additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end, while the back edge is more aerodynamically surface combined with a rear end edge of the washer, the toe is located on the front edge of the end washers below the level of the rear edge and the sweep is 60°-85°.

The invention is illustrated by drawings and schedules.

Figure 1 presents the proposed ending on the side view with the outer side of the end washers;

figure 2 shows a view along arrow a Fig 1;

figure 3 - cross section a-a figure 1;

figure 4 is a top view of the proposed ending;

figure 5 shows the spectra of wrapping the outer surface of the end washers, obtained in the wind tunnel at Mach number M=0.75 and an angle of attack α=4°, which is calculated from the construction plane of the wing (SEC);

figure 6 shows a plot of the averaged angle of bevel of the thread ε the relative height of the end washersbased on the results of the processing of the spectra wrap when M=0.75 and α=4°;

figure 7 presents a diagram of the vector interaction flow with the proposed ending;

on Fig - arrangement of the vortex on the upper surface of the additional aerodynamic surfaces;

figure 9 shows a view along arrow B Fig to plot the distribution of vertical bevels induced conical vortex on the inner side from the axis of the vortex correlated with the plot of the distribution of bevels from vortex inductance;

figure 10 presents in VI is e graphs based glide To the angle of attack α the results of the tests in the wind tunnel model aircraft with the proposed and known back when the Mach number M=0,6;

figure 11 is the same when M=0,7;

on Fig the same when M=0,75;

on Fig the same when M=0,78;

on Fig the same when M=0,8;

on Fig the same when M=0,82.

The wing tip of the aircraft is made in the form of additional aerodynamic surfaces 1 small aspect ratio with a sharp leading edge 2 with sweep χ=60°-85°. Additional aerodynamic surface 1 is mounted on the outer side of the end washers 3 at its end, while the rear edge 4 of the aerodynamic surface 1 combined with the end 5 of the rear edge 6 of the end washers 3. Sock 7 additional aerodynamic surface 1 is located on the front edge 8 of the end washers 3 below the level of the rear edge 4.

The wingtips of the aircraft based on the interaction of additional aerodynamic surface with a field of vertical bevels on the outer side of the end washers.

In the wind tunnel in terms of visualization of experimental studies of vector fields flow from the outer side of the end washers.

After processing the obtained spectra wrap constructed graphs averaged vertical angle ε bevel flow in may the STI height end washers (see Fig.6).

From the experimental dependences shows that the greatest efficiency when installing additional aerodynamic surfaces can be expected in the aerodynamically active zone near the end of the end washers where the vertical bevels maximum.

Vertical bevels Vyhaving a maximum value near the outer surface of the end washers when removing in the direction of the wingspan additional aerodynamic surface rapidly decreases in a hyperbolic law, and the effective area of the vertical angles of the bevel extends up to 0,3-0,35 end of the chord Into. The scope of additional aerodynamic surfaces does not go beyond the specified limits, therefore, the entire area of additional aerodynamic surfaces is in the area of high angles of attack, which is a significant factor in its aerodynamic efficiency.

Separation of flow at the sharp leading edge when χ≥60° transformed into a stable vortex flow with education conical vortex. Increase χ>85°leading to a further reduction of the area of the end of the aerodynamic surface, becomes ineffective.

Additional aerodynamic surface mounted under a negative angle ϕ in relation to conceve is the chord of the wing In to(see figure 1), is in the field of high local angles of attack αmwith respect to the vector of the local velocity VMwhere αm=α+ε.

As a result, a sharp leading edge 2 additional aerodynamic surfaces 1, made with a large sweep under the local angle of attack αmthat is detached thread with the formation of a conical vortex 9, which creates a vacuum in additional aerodynamic surfaces and, accordingly, the lifting force UDP, the projection of which in the direction of flight of the Vis the traction component of T (see Fig.7). Thus, in creating the traction component involved all additional aerodynamic surface on which it is implemented underpressure from vortex 9. The vertical bevels 10 from the inner side from the axis 11 of the vortex 9 the opposite direction to the bevel 12 of the vortex inductance 13, which leads to a reduction of induced drag.

Figure 10-15 positionmarked graphs of the glide angle of attack, K=f(α), obtained from the results of tests in a wind tunnel model of the wing with the proposed tip, position- the prototype model.

From the comparison, it is visible, that the increase is their maximum aerodynamic quality during the transition to the ending, for example for M=0,78, is ΔKmah=0,5.

By increasing the effective sweep system wing - end washer - additional aerodynamic surface increases the critical Mach number (MCR). For example, at high Mach numbers (M=0,8;0,82) increase the maximum glide is ΔKmah=0,2-0,25. Therefore, increasing aerodynamic efficiency of the aircraft To×M, where K - the glide ratio, M is the Mach number.

The proposed solution is a high-tech, has no structural restrictions on the angle of installation of additional aerodynamic surfaces, which, as a rule, chooses the best for cruising flight mode. In addition, the lift coefficient suαadditional aerodynamic surface is lower than for other types of endings, resulting in a minimization of the bending moment on the power structure of the wing. This allows the installation of the proposed ending on existing aircraft without strengthening the main power components of the wing.

Offer ending is essentially integrated, combining the advantages of both vertical end plate, and a horizontal edge lines, allowing to fully implement vertical and horizontal bevels flow in the area of their effective values.

The wing tip of the aircraft, with an end washer, characterized in that it is equipped with additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end, while the rear edge of the additional aerodynamic surfaces combined with a rear end edge of the washer, the toe is located on the front edge of the end washers below the level of the rear edge and the sweep is 60-85°.



 

Same patents:

The invention relates to aviation

The invention relates to aviation, in particular to the training of flight and airplanes

The invention relates to aircraft construction

Aircraft // 2046735
The invention relates to aircraft, and more specifically to methods and devices for modifying the aerodynamic characteristics of the aircraft and stabilizing surfaces, mounted on the wings

Flying vehicle wing // 2264327

FIELD: aviation.

SUBSTANCE: proposed flying vehicle wing is sweep-back wing with tips of the same sweep. Tips are directed forward against flow in sweep-forward position Xt.l.ed.<0 at retained geometric parameters of wing: wing area, span, aspect ratio and parallelism of tip chord of wing plane of symmetry, where Xt.l.ed. is sweep angle over leading edge of wing tips.

EFFECT: increased carrying properties of wing sweep over entire range of velocity head; enhanced efficiency of ailerons at moderate and high velocity heads.

9 dwg

Aircraft wing // 2254266

FIELD: aviation.

SUBSTANCE: proposed aircraft wing has inner load-bearing primary structure and upper and lower skins. Wing is made in form of chute of varying section in plan smoothly narrowing from aircraft nose to tail.

EFFECT: updated wing differing from tear-shaped wing; enhanced efficiency of creating lifting force.

4 dwg

Swept wing // 2216481
The invention relates to aeronautical engineering

The invention relates to aviation

The plane // 2213023
The invention relates to aircraft construction

The invention relates to aviation, in particular to the training of flight and airplanes

The invention relates to aircraft and can be used on the aircraft, subsonic and transonic flight speeds

The invention relates to aviation

The invention relates to the triangular wings with reverse narrowing and their modifications, and in particular to the triangular wings with reverse narrowing for supersonic aircraft

Supersonic aircraft // 2100253

Aircraft wing // 2254266

FIELD: aviation.

SUBSTANCE: proposed aircraft wing has inner load-bearing primary structure and upper and lower skins. Wing is made in form of chute of varying section in plan smoothly narrowing from aircraft nose to tail.

EFFECT: updated wing differing from tear-shaped wing; enhanced efficiency of creating lifting force.

4 dwg

Flying vehicle wing // 2264327

FIELD: aviation.

SUBSTANCE: proposed flying vehicle wing is sweep-back wing with tips of the same sweep. Tips are directed forward against flow in sweep-forward position Xt.l.ed.<0 at retained geometric parameters of wing: wing area, span, aspect ratio and parallelism of tip chord of wing plane of symmetry, where Xt.l.ed. is sweep angle over leading edge of wing tips.

EFFECT: increased carrying properties of wing sweep over entire range of velocity head; enhanced efficiency of ailerons at moderate and high velocity heads.

9 dwg

FIELD: aeronautical engineering; various flying vehicles.

SUBSTANCE: proposed tip has end plate and is provided with additional swept aerodynamic surface of low aspect ratio with sharp leading edge mounted on the outside of end plate. Trailing edge of additional aerodynamic surface is combined with trailing edge of end plate. Nose is located on leading edge of end plate below level of trailing edge; sweep ranges from 60° to 85°.

EFFECT: enhanced aerodynamic efficiency at high subsonic speeds.

15 dwg

FIELD: aeronautical engineering; lifting surfaces of various-purpose flying vehicle.

SUBSTANCE: proposed tip has swept aerodynamic surface whose lower plane is formed by smooth extension of generatrices of wing lower surface. Nose of root chord of end aerodynamic surface is located on lower contour of wing end profile at point of intersection with line of maximum thicknesses. Leading edge of end aerodynamic surface is sharp in contour and is located on one line with wing trailing edge; upper plane of end aerodynamic surface is made with smooth change at point of connection with wing. End aerodynamic surface has low aspect ratio and its sweep ranges from 60 to 85°.

EFFECT: improved aerodynamic property at high subsonic flight speeds.

10 dwg

Flying vehicle wing // 2266233

FIELD: aviation.

SUBSTANCE: proposed swept-forward wing has tips of the same sweep. Tips are turned backward in flow to sweep-back position at retained parameters of swept wing and parallelism of tip chord of wing plane of symmetry.

EFFECT: reduction of aeroelastic deformation and avoidance of divergence at high velocity heads on metal swept-forward wing.

6 dwg

Flying vehicle wing // 2272745

FIELD: aeronautical engineering; lifting surfaces of various flying vehicles.

SUBSTANCE: proposed flying vehicle wing has additional aerodynamic surface in form of plate mounted on it. Plane is triangular in plan and its end edge is sharp and is parallel to wing axis of symmetry. Plate is located at distance from tip chord equal to 0.05-0.1 of wing span and its length is equal to 0.1-0.15 of wing chord at point of location of end edge of additional aerodynamic surface. Trailing edge of additional aerodynamic surface is rectilinear in form. Its upper surface is formed by extension of upper surface of wing and lower surface is smoothly conjugated with lower profile of wing tail section.

EFFECT: extended field of application; improved aerodynamic properties.

10 dwg

Up!