﻿ 超临界机翼的静气动弹性特性研究

# 超临界机翼的静气动弹性特性研究Investigations of Static Aeroelasticity Characteristics for Supercritical Wing

Abstract: Coupling with static aeroelastic balancing equation, the time domain calculation method of static aeroelastic deformation is developed using the structure influence coefficient method. Firstly, the static aeroelastic deformation of medium aspect ratio swept-back wing was simulated using the developed method. Computational results are in good agreement with those of other literatures and experimental results. The static aeroelasticity calculation method is feasible. Then, the aerodynamic force of supercritical wing and common wing is calculated by 3-D Euler equations with cell-centered finite-volume algorithm, explicit Runge-Kutta time stepping scheme. The static aeroelasticity characteristics of supercritical wing are summarized by comparison and analysis of computational results. The characteristics supply some academic foundations for design of supercritical elastic wing and improving aerodynamic characteristics of supercritical elastic wing.

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