摘要
针对现代民用飞机设计巡航阻力预测中不考虑转捩影响很难完善计算与试验对比的问题,采用固定转捩和全湍流方法完成DLR_F4翼身组合体阻力计算,并与试验及相关文献结果进行对比.结果表明:采用设置有小范围层流区的固定转捩计算与相应全湍流计算得到的压力因数分布基本一致,二者之间总阻力的差量主要表现在黏性阻力方面;在大多数迎角下,全湍流计算结果与试验比较接近,只在大迎角接近失速时,全湍流结果稍差;2种计算方式对评估带有小范围层流区风洞试验的阻力结果有积极意义.
As to the problem that the comparison of calculation and test is difficult to be improved in drag calculation of civil aircraft without considering transition effect,the drag of DLR_F4 wing-body is respectively calculated by fix transition method and full turbulence method,and the results are compared with test results and the results of some literatures.The comparison indicates that,the pressure factor distributions obtained by the two methods are basically consistent with each other,and the main difference of the total drag between them lies in viscous drag;the results of full turbulence method are close to the test results under most attack angles,and only when the high attack angles is close to stall,the results become a little worse;both methods can provide reference for the evaluation of drag results in tunnel test with a small laminar area.
出处
《计算机辅助工程》
2011年第4期72-76,共5页
Computer Aided Engineering
