Optimization design method for wing types of low-Reynolds-number staggered-floor wings

Abstract

The invention discloses an optimization design method for wing types of low-Reynolds-number staggered-floor wings, and belongs to the technical field of flight vehicle design. Specific to the staggered-floor wings, the wing types are subjected to parameterization by adopting an NURBS curve fitting method, and 13 control points are selected on front and back wings for control separately; computational grids are generated by adopting an automatic grid reconstruction technology, and numerical value simulation on a flow field is carried out based on a <gamma>-Re<theta> transition model which is coupled with a k-<ohms> SST turbulence model; and optimization is carried out by a combined optimization strategy by combination of DOE sampling and a multi-island genetic algorithm as follows: uniform sampling in a designed space is performed by optimal Latin hypercube design, an most effective design region in the overall design space is captured, and then optimization design is performed in the most effective design region by adopting the multi-island genetic algorithm. By performing optimization on the wing types of the staggered-floor wings, unfavorable pneumatic interference of the staggered-floor wings is lowered, lift-drag ratio is improved, the calculated amount is reduced on the basis of ensuring the calculation precision, and the optimization efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft design and relates to aerodynamic optimization design, in particular to an airfoil optimization design method for a low Reynolds number staggered wing. Background technique [0002] A split wing is a wing layout composed of two airfoils, the front wing and the rear wing, such as figure 1 As shown, the front wing 1, the rear wing 2 and the fuselage 3 on both sides form a box structure. The horizontal and vertical positions of the front wing 1 and the rear wing 2 are different. This wing layout is conducive to load bearing due to the sharing of the lift force between the front wing and the rear wing and the increase in the overall structural height and width of the wing. It has the characteristics of high rigidity and light weight, and the maximum geometric size of the wing can also be reduced. Thereby reducing the requirements on the airport runway. However, due to the complex flow field formed...

AI Technical Summary

Problems solved by technology

The interference between the two airfoils makes the flow around it different from that of a single wing, so it is necessary to carry out a collaborative optimization design for the front and rear airfoils according to the respective working conditions of the front and rear wings, which also doubles the number of design variables

In addition, the flow washing effect of the split wing varies with the wing difference angle and relative position, which makes the optimization of the split wing different from the conventional single airfoil, and there is no mature and practical optimization method at present.

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