Aerodynamic optimization method of leading edge slats position and trailing edge flap position of two-dimensional three-section airfoil profile

Abstract

The invention discloses an aerodynamic optimization method of a leading edge slats position and a trailing edge flap position of a two-dimensional three-section airfoil profile. The method takes the translational motion amounts, which are relative to the original positions of a leading edge slats and a trailing edge flap of a two-dimensional three-section airfoil profile, of the leading edge slats position and the trailing edge flap of the two-dimensional three-section airfoil profile and the rotation amounts obtained by the in-plane rotation around the independent leading edge point of the leading edge slats position and the trailing edge flap as optimal design variables, and takes a situation that whole airfoil profile aerodynamic performance is improved after the translation motion and the rotation of the leading edge slats and the trailing edge flap as an optimization target. The aerodynamic optimization method adopts a nesting double-circulation optimization flow to effectively solve the problems of low optimization efficiency, high computation frequency and long computation time consumption caused by high design variable spatial dimension and large search range in an optimization design process of the two-dimensional three-section airfoil profile, wherein the external circulation of nesting double-circulation optimization flow contains sensitivity analysis, and the internal circulation of the nesting double-circulation optimization flow takes a genetic algorithm as an optimization algorithm. The method automatically dispatches a computation node in a parallel computation environment through a workflow engine, and automatically dispatches the parallel computation to fully utilize computation resources, shorten total computation time required by the optimization process and improve optimization efficiency.

Description

technical field [0001] The invention relates to an aerodynamic optimization method for the positions of leading edge slats and trailing edge flaps of a two-dimensional three-segment airfoil, which belongs to the technical field of aircraft two-dimensional airfoil aerodynamic optimization. Position optimization of leading edge slats and trailing edge single-slot flaps in any downflow profile. Background technique [0002] The main flight stages of modern civil airliners include take-off, landing and cruise. The flight speeds of modern civil airliners are different in each flight stage. Therefore, in order to ensure their basic flight performance and reduce flight costs during the flight, modern civil airliners There are different requirements for the lift coefficient, drag coefficient and pitch moment coefficient of passenger aircraft wings in each flight phase. Usually, the flight speed of civil passenger aircraft is higher in the cruising stage, and the flight speed in the...

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Problems solved by technology

[0007] The present invention is designed to provide a two-dimensional three-section airfoil leading edge slat and trailing edge flap position aerodynamic optimization method aimed at the above-mentioned prior art situation, and its purpose is to solve the problem of the passenger aircraft wing lift device for different Optimization problem of optimal position of leading-edge slats and trailing-edge flaps during flight phase

In the optimization process, the nested double-loop optimization process is adopted to solve the problems of large optimization population size, many calculation times, and long calculation time caused by the high latitude of the global design space, large search space, and large optimization population in the optimization calculation.

This method is applied to the optimization platform, adopts automated workflow, can solve the problem of insufficient hardware and software resources through parallel computing, and improve optimization efficiency

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