Variable wing leading edge combining subsonic aerodynamic performance and supersonic aerodynamic performance

Abstract

The invention discloses a variable wing leading edge combining subsonic aerodynamic performance and supersonic aerodynamic performance, and belongs to the technical field of aerodynamic design of aircrafts. The variable wing leading edge is formed by mounting two movable leading edge baffles on the upper and lower sides of the wing leading edge through connecting rods respectively, and the two movable leading edge baffles make contact to form a sharp wing leading edge during supersonic flight; during subsonic flight, the two movable leading edge baffles translate forwards and rotate respectively to expose the wing leading edge, and an open slot structure is formed between each movable leading edge baffle and the wing leading edge. By means of the variable wing leading edge, the shape of the wing leading edge can be changed reasonably by the two movable leading edge baffles according to different environments in a flight process of an aircraft, the aircraft can obtain higher lift-drag ratio in supersonic and subsonic flight states, and use cost can be reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft aerodynamic design, and relates to a variable wing leading edge that takes into account both subsonic and supersonic aerodynamic performances, in particular to a wing leading edge that adopts a variable geometric shape to improve the performance of an aircraft against subsonic and supersonic speeds. Adaptability to sonic flight conditions, taking into account the design of aerodynamic efficiency in different flight conditions. Background technique [0002] In order to reduce the impact of sonic booms generated during flight on people’s lives, aircraft are expressly prohibited from flying at supersonic speeds over human-inhabited areas. Capable aircraft can only fly at subsonic speeds in such areas. The ability of aircraft to fly at supersonic speed is mostly reflected by the sharp wing leading edge of the wing, and the radius of the wing leading edge of this sharp wing leading edge wing can be r...

AI Technical Summary

Problems solved by technology

When the aircraft is flying at a subsonic speed, the airflow above the stagnation point on the surface of the sharp wing leading edge must move upward to bypass the sharp wing leading edge, and the sharp wing leading edge with an infinitely small radius of the wing leading edge will cause the air flow to The surface of the sharp wing leading edge separates to produce leading edge separation bubbles, and the leading edge separation bubbles will be generated at a very small angle of attack, so the subsonic lift-drag ratio of such sharp wing leading edge aircraft is also comparable. The lower the aerodynamic efficiency of the aircraft during subsonic flight, the lift-to-drag ratio can only reach a fraction of that of a wing with a blunt wing leading edge, and the fuel consumption of the aircraft will increase greatly, which is not conducive to reducing The cost of using the aircraft

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