摘要
音爆的预测是超声速民用飞机设计的关键技术。采用多块结构化网格有限体积法求解Euler/N-S控制方程,对SeebALR旋成体和三角翼两个典型低音爆构型国际标准算例的近场音爆进行了计算,与风洞试验数据进行了对比分析。结果表明,对于上述标准算例的简单绕流场进行近场音爆计算时,流场黏性效应不是必须考虑的因素;随着方位角的变化,三角翼尾部激波从单个激波演变为多激波;来流攻角的变化不影响头部激波强度,机翼前缘激波强度随攻角的增加而逐渐增强。
Sonic boom prediction is a key issue to be addressed in supersonic commercial transport design. The finite volume method base on multi-block structured girds was applied to solve Euler/N-S governing equations for predicting near field signatures of sonic boom. Two benchmark cases of typical LSB （Low Sonic Boom） configurations were calculated, including SEEB-ALR model and Delta wing model. The predicted results were compared with experimental data. The results show that Navier-Stokes computations are not always necessary for simple flow-fields. The tail shock changes from a single to multiple-shock waveform from on-track to off-track. There is very few influence of the attack of angle on the intensity of the bow shock. The shock starting from the leading edge of wing becomes stronger as the attack of angle increases.
出处
《航空科学技术》
2016年第7期12-16,共5页
Aeronautical Science & Technology
关键词
超声速客机
音爆
低音爆构型
近场
激波
supersonic airliner
sonic boom
LSB configuration
near field
shock wave
作者简介
通讯作者：徐悦（1979-）男，博士，高级工程师。主要研究方向：气动芦哮，Tel：010—84933571 E-mail：xuyue@cae．ac．cn
