不确定性飞行环境中动态激波控制鼓包减阻机制研究

项目名称： 不确定性飞行环境中动态激波控制鼓包减阻机制研究

项目编号： No.11502112

项目类型： 青年科学基金项目

立项/批准年度： 2016

项目学科： 数理科学和化学

项目作者： 邓枫

作者单位： 南京航空航天大学

项目金额： 20万元

中文摘要： 大型客机高速飞行时机翼上出现的激波是阻碍其气动效率提高的主要因素之一。近年来所发展的二维/三维静态激波控制鼓包技术经证实可以有效削弱理想设计条件下机翼上激波的强度，从而降低飞行阻力，但在非理想设计条件下由于受控激波位置和强度的不确定性，减阻效果有限。为此，本项目针对真实飞行环境中存在的不确定性，提出将二维/三维静态激波控制鼓包的概念扩宽到四维动态激波控制鼓包，通过增加时间维度的变化，根据受控激波的变化形态调整鼓包的外形，从而有效的对较宽飞行范围内的动态激波进行控制，以进一步提升鼓包技术的鲁棒性和实用价值，为下一代智能机翼的研制提供理论依据。本研究将以基于求解非定常雷诺平均Navier-Stokes方程的数值模拟和高效的全局数值优化方法为手段，将针对不确性飞行环境中非定常激波在动态鼓包的激励作用下，激波的结构形态、控制之后波系结构的稳定性以及激波控制过程中的非定常效应这几个方面重点开展研究。

中文关键词： 跨音速；激波；；激波控制鼓包；减阻；不确定性

英文摘要： The shock waves appeared on the wings of civil transports flying at the high speeds are one of the main reasons causing their poor performance. In recent years, a kind of shock control device called Shock Control Bump has been proved to be able to dramatically reduce the wave drag under ideal conditions. To further improve its robustness, a new concept called Dynamic Shock Control Bump has been proposed to weaken the unsteady shock waves on the wings under uncertain flight conditions. By adopting the high-fidelity numerical simulation method based on solving the unsteady Reynolds-averaged Navier-Stokes equations and an efficient global numerical optimization algorithm based on the Kriging model, this research will focus on: 1) the flow pattern of the unsteady shock waves controlled by dynamic shock control bumps; 2) the stability of the unsteady shock waves under control; 3) the unsteady effects caused by the movements of dynamic shock control bumps. The goal of this project is to reveal the flow physics of the dynamic shock control bumps, which will finally inspire the development of the next generation intelligent wings.

英文关键词： Transonic;shock wave;Shock control bump;drag reduction;uncertainty