阅读说明：本技术 飞行器的流动本体及飞行器 (Flow body of aircraft and aircraft ) 是由 彼得·克罗伊策 于 2019-07-26 设计创作，主要内容包括：一种飞行器的流动本体(10),包括：流动表面(11),所述流动表面在所述飞行器的飞行期间暴露于气流中,所述流动表面(11)在所述飞行器的飞行期间产生至少一个湍流空气流的区域(24),至少一个穿孔区域,所述至少一个穿孔区域包括延伸穿过所述流动表面(11)的多个开口(32),集流腔(14),所述集流腔被定位在所述流动表面(11)的内部、与所述开口(32)处于流体连通,以及至少一个抽吸管(28),所述抽吸管具有第一端部(27)和第二端部(29),所述第一端部(27)与所述集流腔(14)处于流体连通,所述第二端部(29)包括抽吸开口(20)、并且安排在所述至少一个湍流空气流的区域(24)中,其中,所述抽吸开口(20)被适配成用于当在飞行期间所述流动表面(11)暴露于气流时在所述至少一个抽吸管(28)中引起抽吸,由此引起穿过所述多个开口(32)的空气流。本发明提供一种具有改善的空气流的流动本体(10)。(A flow body (10) of an aircraft, comprising: a flow surface (11) exposed to an airflow during flight of the aircraft, the flow surface (11) generating at least one region (24) of turbulent airflow during flight of the aircraft, at least one perforated region comprising a plurality of openings (32) extending through the flow surface (11), a manifold (14) positioned inside the flow surface (11) in fluid communication with the openings (32), and at least one suction duct (28) having a first end (27) and a second end (29), the first end (27) being in fluid communication with the manifold (14), the second end (29) comprising a suction opening (20) and being arranged in the at least one region (24) of turbulent airflow, wherein the suction opening (20) is adapted for inducing suction in the at least one suction duct (28) when the flow surface (11) is exposed to an airflow during flight, thereby inducing an airflow through the plurality of openings (32). The invention provides a flow body (10) with improved air flow.)

1. A flow body (10) of an aircraft, the flow body comprising:

a flow surface (11) exposed to an airflow during flight of the aircraft, the flow surface (11) generating at least one region (24) of turbulent airflow during flight of the aircraft,

at least one perforated area comprising a plurality of openings (32) extending through the flow surface (11),

a manifold (14) positioned inside the flow surface (11), in fluid communication with the opening (32), and

at least one suction duct (28) having a first end (27) and a second end (29), said first end (27) being in fluid communication with said manifold (14), said second end (29) comprising a suction opening (20) and being arranged in said at least one region (24) of turbulent air flow,

wherein the suction opening (20) is adapted for inducing a suction force in the at least one suction duct (28) when the flow surface (11) is exposed to an airflow during flight, thereby inducing an airflow through the plurality of openings (32).

2. The flow body according to claim 1, wherein the flow body (10) comprises a plurality of suction tubes (28).

3. The flow body according to claim 2, wherein the flow surface (11) generates a plurality of mutually spaced areas (24) of turbulent air flow during flight of the aircraft, and wherein the plurality of suction pipes (28) are separately arranged in the plurality of areas (24) of turbulent air flow.

4. The flow body according to claims 2 to 4, wherein the manifold (14) comprises a plurality of manifold segments (16), wherein each manifold segment of the plurality of manifold segments (16) is arranged on a separate portion of the at least one perforated region.

5. The flow body according to claim 4, wherein the plurality of suction tubes (28) and the plurality of manifold segments (16) are associated with each other in a one-to-one ratio.

6. The flow body according to claim 4 or 5, wherein the manifold segments (16) are separated by walls (26).

7. The flow body according to claim 6, wherein the walls (26) provide a gas-tight seal between the manifold sections (16).

8. Flow body according to one of claims 1 to 7, wherein each of the at least one suction duct (28) comprises a section adapted to the pressure value at the location of the suction opening (20) in the region (24) of turbulent air flow.

9. The flow body according to one of claims 1 to 8, wherein the flow surface (11) comprises turbulence generating structures (22) which generate the at least one region (24) of turbulent air flow.

10. Flow body according to one of claims 1 to 9, wherein the flow body (10) is an airfoil, such as an aircraft wing (12), winglet (37), vertical tail (36), or horizontal tail (38).

11. The flow body according to claim 10, wherein the flow body (10) comprises a leading edge (18) facing the airflow during flight, wherein the at least one perforated area is arranged at the leading edge (18).

12. The flow body according to claim 10 or 11, wherein the flow body (10) is an airfoil, the airfoil comprising a lift enhancing device (30) arrangeable in the manifold (14), wherein the lift enhancing device is preferably a krueger lift enhancing device.

13. An aircraft (40) comprising at least one flow body (10) according to one of claims 1 to 12.