Drag reduction needle passive control method and device for wing shockwave control

Abstract

Relating to the technical field of shockwave control, the invention discloses a drag reduction needle passive control device for wing shockwave control. The device specifically includes aircraft wings and drag reduction needles arranged on the aircraft wings. The drag reduction needles are fixed in shockwave areas on the upper surfaces of the aircraft wings, the drag reduction needles are L shaped, and one ends of the drag reduction needles are vertically fixed at the shockwave areas on the upper surfaces of the aircraft wings. Through mutual interference of the drag reduction needles placed at the shockwave areas on the upper surfaces of the aircraft wings and initial strong normal shockwaves, a series of oblique shockwaves are generated to replace the initial normal shockwaves so as to reach the purpose of weakening wave drag.

Description

technical field [0001] The invention relates to the technical field of wing shock wave control, and discloses a drag reducing pin passive control method and device for wing shock wave control. Background technique [0002] The requirements of large aircraft for carrying capacity, long range, long endurance and fast transport capability determine that it must have high lift, high aerodynamic efficiency, high flight speed and low fuel consumption. The lift of the aircraft mainly comes from the wings, low fuel consumption corresponds to low resistance, and aerodynamic efficiency is the product of the flight Mach number and the lift-to-drag ratio. Therefore, modern advanced large aircraft require advanced wing technology with small resistance, high cruise lift-to-drag ratio (ratio of lift to drag), and high cruise aerodynamic efficiency. Supercritical wing technology is a wing technology commonly used and applied in modern large aircraft. [0003] The force of the air against ...

AI Technical Summary

Problems solved by technology

At present, many optimization measures have been studied, such as passive ventilation of the cavity under the shock wave, cavity suction / jet, return plate, solid bulge or adaptive wing bulge, etc. The method of passive ventilation to weaken the shock wave has been developed in the past 20 years. It has been extensively researched for many years, but that method only achieves the purpose of reducing drag in some specific flight conditions. In most flight conditions, it reduces wave resistance while increasing viscous drag, and instead reduces the total drag. Increase

Solid bulges or adaptive wing bulges have a good effect of reducing shock wave resistance at the design point, but their drag reduction effect is very sensitive to parameters, causing large changes to the aerodynamic characteristics of the airfoil at non-design points, and the bulge is easy to induce local separation flow

At the same time, the control strategies of these methods are all directly acting on the surface of the aircraft, which has a great impact on the aerodynamic characteristics of the original wing. It is necessary to evaluate and correct the overall aerodynamic layout, which is not conducive to the modification of existing mature aircraft.

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