翼型改型对超临界翼型气动性能影响的数值研究  

Effect numerical study of modified airfoil on aerodynamic performance of supercritical airfoil

作　　者：陆超[1] 徐志晖[1] 张广[1] 

机构地区：[1]沈阳航空工业学院动力与能源工程学院,辽宁沈阳110136

出　　处：《沈阳航空工业学院学报》2008年第5期32-35,共4页Journal of Shenyang Institute of Aeronautical Engineering

摘　　要：为了深入研究改型对跨声速翼型气动性能的影响,对NASA SC(2)-0614翼型进行多种方案的改型,包括前缘半径、厚度、弯度、翼型上表面形状等,并得出最终优化改型方案。数值模拟结果表明,改型后翼型设计状态下升阻比和临界马赫数均有显著提高。This paper investigated the effect of several modifications of NASA SC （2） -0614 airfoil, including leading edge radius, thickness, curvature and suction surface of the airfoil, etc. , including its aerodynamic performance and final modified airfoil optimization . The numerical simulation show that the lift drag coefficient and critical March number has increased significantly for the modified airfoil at the design point.

关 键 词：超临界翼型 临界马赫数 升阻比 

分 类 号：V211.412[航空宇航科学与技术—航空宇航推进理论与工程]