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Supersonic annular wing design method

A design method and ring wing technology, applied in aerospace and aviation fields, can solve problems such as damage to the design state

Inactive Publication Date: 2019-05-28
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the ring-shaped Busman wing does not consider that a certain angle of attack is required to generate lift, which will destroy the best design state

Method used

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Embodiment Construction

[0029] specific implementation plan

[0030] This embodiment is a supersonic annular wing design method.

[0031] refer to Figure 1 to Figure 7 , the supersonic annular wing design method in this embodiment uses computational fluid dynamics technology to numerically simulate the flight conditions of the airfoil; the governing equation is the Euler equation.

[0032] The airfoil is an annular variable-section Lischer wing, and the specific design scheme is as follows:

[0033] Firstly, the relative thickness of the airfoil is designed to obtain the wedge angle ε, and then the design Mach number M is given a The shock angle β is obtained, the distance z between the two wings is obtained from the shock angle, and the Bussmann double-wing configuration is obtained, at this time t 1 = t 2 =t, c is the chord length, and t is the thickness of the wings.

[0034]

[0035] Then design the angle of attack α of the airfoil when cruising, and calculate the design parameters of th...

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Abstract

The invention discloses a supersonic annular wing design method, and relates to the technical fields of aeronautics and astronautics. The supersonic annular wing design method is characterized in thatbased on the design of an annular Bossman wing, an annular ReZEL wing is proposed in combination with the design of a ReZEL wing. The design of the ReZEL wing is to skive an upper triangular unit tobe thin and thicken a lower triangular unit, so that an expansion wave position of a shock wave between double wings reaches a design state; four connecting supports are located at positions which areat 45 degrees with a horizontal plane and a vertical plane of the annular wing; the four connecting supports have a same radius; and the connecting supports are used for connecting an outer annular wing and an inner annular wing. During a cruise phase, the annular ReZEL wing can generate lift force at zero angle of attack and have greater lift force at different angles of attack; the lift-to-dragratio is significantly increased, so that better flight performance can be obtained.

Description

technical field [0001] The invention relates to the technical field of aviation and spaceflight, in particular to a three-dimensional supersonic annular variable-section wing. Background technique [0002] The greatest resistance produced by an aircraft during supersonic cruise is shock wave resistance. Excessive shock wave resistance will lead to adverse effects such as reduced cruising speed, shortened voyage, and increased cost; therefore, reducing shock wave resistance can greatly improve the performance of supersonic aircraft. performance. [0003] At the 38th International Conference on Aerodynamics in 2008, Israeli aerodynamicist Yi Guerra proposed a ring-shaped Busman biplane. The design idea of ​​Bussmann's wings is to divide the rhombus wing into two triangular units and place them opposite each other. With the selected design parameters, the shock wave generated by the leading edge just hits the thickest part of the airfoil, and the thickest part of the airfoil ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/10B64C3/14B64C3/38B64C3/36B64F5/00
Inventor 王刚周泽堃马博平刘奇武洁叶正寅
Owner NORTHWESTERN POLYTECHNICAL UNIV
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