CAJ | 학술논문

针对超临界翼型的流动特征，利用计算流体力学方法，通过典型算例开展了对多鼓包技术流动机理与减阻特性的研究。首先对超临界翼型的绕流特征进行了分析，在流动发生转捩的前缘区域布置鼓包，改善翼型前段的压力梯度，减小湍流粘性，达到减阻的目的。然后在典型超临界翼型RAE2822上，研究了前缘鼓包与激波鼓包分别单独作用时，其几何外形和位置参数对减阻的影响。最后对前缘鼓包、激波鼓包的位置和形状参数进行了协同调整，研究了前缘鼓包对常用激波鼓包的减阻效果的影响。经计算，前后鼓包共同减阻的效果确实优于单独激波鼓包，最大减阻量可达11．5％。
침대초림계익형적류동특정，이용계산류체역학방법，통과전형산례개전료대다고포기술류동궤리여감조특성적연구。수선대초림계익형적요류특정진행료분석，재류동발생전렬적전연구역포치고포，개선익형전단적압력제도，감소단류점성，체도감조적목적。연후재전형초림계익형RAE2822상，연구료전연고포여격파고포분별단독작용시，기궤하외형화위치삼수대감조적영향。최후대전연고포、격파고포적위치화형상삼수진행료협동조정，연구료전연고포대상용격파고포적감조효과적영향。경계산，전후고포공동감조적효과학실우우단독격파고포，최대감조량가체11．5％。
We study the flow characteristics of supercritical airfoil;we have tested some classic examples to explore the flow mechanism of multi-bump technology and to study the characteristics of drag reduction by taking advantage of Computational Fluid Dynamics ( CFD) method.We analyze the flow mechanism of multi-bump and then adjust the location and the geometry of multi-block .We find that not only the bump near the shock can reduce the wave drag but also the bump located near the leading-edge can improve the flow properties of airfoil .We applied multi-bump technology to RAE2822,and we find that the multi-bump technology can get more drag reduction ,and that the total drag reduction can reach 11.5%.