前缘网格分布对超临界机翼低速气动特性影响研究

摘要

生成合理的计算网格是保证数值模拟精度和准确度的前提条件.超临界机翼前缘半径较大且流场变化剧烈,机翼前缘的网格分布对超临界机翼的低速气动特性的数值模拟有重要影响.通过对同一构型不同机翼前缘网格分布进行数值模拟,研究了前缘网格密度对超临界机翼失速攻角、最大升力系数和分离形态的影响.结果表明,随着机翼前缘网格密度的提高,该构型的失速攻角、最大升力系数都有显著的提高；机翼的分离形态发生本质变化,由外翼先分离变为内翼先分离.%Generating reasonable grid is the precondition to guaranty the precision and validity of numerical simulation. The leading edge radius of the supercritical wing is bigger than other types and the flow field near the leading edge changes remarkably. The leading edge grid distribution has great influence on the low speed characteristics of supercritical wing. Influence of different leading edge grid distribution on the stall angle of attack, maximum lift coefficient and separation form is investigated through numerical simulation of one supercritical wing. Simulation results indicate that the stall angle of attack and maximum lift coefficient are greatly increased by increasing the leading edge grid. The separation form of the supercritical wing changes essentially from the outboard to the inboard.