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.
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
关键词
超临界翼型
临界马赫数
升阻比
supercritical airfoil
critical march number
lift drag coefficient
