边条机翼布局战斗机稳定性改进研究  

Investigation on the Improvement of Stabilities of Combat Aircraft with Strake Wing Configuration

作　　者：钱丰学[1] 梁贞桧[1] 

机构地区：[1]中国空气动力研究与发展中心高速所,四川绵阳622661

出　　处：《飞行力学》2002年第2期55-57,61,共4页Flight Dynamics

摘　　要：对边条机翼布局战斗机的纵、横向稳定性改进措施进行了研究。结合具体战斗机布局 ,给出了边条机翼布局战斗机纵、横向稳定性的一般特征 ,对前缘襟翼下偏、翼刀、平尾下反和机身截面修形等几种气动布局改进措施的风洞试验结果进行了简要讨论。结果表明 ,所研究的气动布局改进措施都能有效提高边条机翼布局战斗机的稳定性 ,其中 ,前缘襟翼下偏既能完全克服俯仰力矩曲线非线性上翘问题 。Some measures improving the longitudinal and lateral stabilities of combat aircraft with strake wing configuration are discussed.Based on the specific combat aircraft model,the general longitudinal and lateral stabilities characteristics of combat aircraft with strake wing configuration are analyzed,and wind tunnel test results of some improvement measures,such as leading edge flap deflection,wing fence,horizontal tail downward dihedral and body section modification,are discussed briefly.The test results of the measures show that all of these are efficient for improving the stabilities of combat aircraft with strake wing configuration.Moreover, the conclusion that the problem of pitch moment curve up warp at moderate angle of attack and the difficulty of lateral stability upset at high angle of attack can be solved by the down deflection of leading edge flap can be successfully drawn from the context.

关 键 词：边条机翼 战斗机 稳定性 气动布局 俯仰力矩特性 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] V212.1