Vortex generator for reducing resistance of fuselage and delaying airflow separation

Abstract

The embodiment of the invention discloses a vortex generator for reducing resistance of a fuselage and delaying airflow separation, and relate to the technical field of rotor aircraft manufacturing. According to the vortex generator, the passive control for the flowing of a flow field near the fuselage can be realized when a rotor aircraft encounters strong cross-wind or carries out side flight, so that the resistance of the rotor aircraft is reduced, and meanwhile, the implementation cost and the failure rate are reduced. The vortex generator provided by the invention comprises an installation angle (2) of the vortex generator, a first corner (9) of a single-chip vortex generator and a second corner (20) of the single-chip vortex generator, wherein a value of the installation angle (2) ofthe vortex generator is larger than or equal to 10 degrees and less than or equal to 45 degrees; the second corner (20) of the single-chip vortex generator is an included angle between an upper surface (7) of the second section and a connecting section (19) of the vortex generator and the object surface; a value of the first corner (9) of the single-chip vortex generator is less than 30 degrees;and a value of the second corner (20) is larger than or equal to 40 degrees and less than or equal to 60 degrees. The vortex generator is suitable for the passive control for the flow of the flow field near the fuselage when the rotor aircraft encounters the strong cross-wind or carries out side flight.

Description

technical field [0001] The invention relates to the technical field of rotorcraft manufacturing, in particular to a vortex generator used for reducing drag on a fuselage and delaying airflow separation. Background technique [0002] In many application fields, rotorcraft is irreplaceable. With the continuous improvement of the speed of the rotorcraft, it is more and more important to reduce the drag of the rotorcraft. Generally speaking, the waste drag of the rotorcraft fuselage can account for 25% to 30% of the total aircraft waste drag, so it is very necessary to carry out drag reduction work on the rotorcraft fuselage. [0003] Among them, the crosswind flow is a more difficult problem in the drag reduction design of the rotorcraft. When the rotorcraft is in the crosswind flow situation, the fuselage in this state is not streamlined relative to the incoming flow. At this time, the flow field of the fuselage is easy. A large airflow separation area occurs, which greatly ...

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Problems solved by technology

[0003] Among them, the crosswind flow is a more difficult problem in the drag reduction design of the rotorcraft. When the rotorcraft is in the crosswind flow situation, the fuselage in this state is not streamlined relative to the incoming flow. At this time, the flow field of the fuselage is easy. A large airflow separation area occurs, which greatly increases the resistance of the fuselage and the power consumption of the rotor, and even leads to a crash. Therefore, it is very necessary to carry out drag reduction work on the rotorcraft fuselage when the crosswind is coming.

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