Aerodynamic design of convertible prop-rotor is a challenging and complex task.Instead of focus on a design condition,prop-rotor are requested to attain good performance in wide range of operating conditions.In present work,to further improve performance of prop-rotor under each operating condition,the concept of variable-pitch proprotor has been proposed.However,a compromising aerodynamic design of prop-rotor is inevitable,due to discrepancy of operating condition.Consequently,a multi-objective optimization is implemented with genetic algorithm.Factors which has significantly influenced on aerodynamic characteristics of prop-rotor are employed as design variable.To avoid expensively computational cost,two theories has been implemented and validated while it able to provide a promising result without high consuming of time.Eventually,several designed individuals within different performance has been analyzed and discussed.Subsequently a calculation of aerodynamic characteristic with hi...

基于"第一届CHN-T1标模CFD可信度研讨会"的相关计算安排,采用CFL3D求解器结合组委会提供的结构网格进行CHN-T1标模的气动特性计算。对比发现CFL3D求解器的SST湍流模式相对SA模式具有更好的网格收敛性。对标模的抖振特性进行了分析,发现抖振起源于机翼中段的激波/边界层干扰,进入抖振状态后当迎角继续增大,激波将持续增强,同时外翼段的后加载减小,使得低头力矩下降,操纵特性变差。对静气弹效应进行了分析,发现该效应主要影响了变形较大位置的升力系数以及激波强度。大雷诺数下机翼截面压力分布后加载包围的面积增大,机翼上表面超声速区的吸力平台有所下降。