学术论文

      典型低音爆构型的近场音爆计算研究

      Near Field Sonic Boom Calculation on Typical LSB Conifgurations

      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Seeb-ALR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。
      Abstract:
      Sonic boom prediction is a key issue to be addressed in supersonic commercial transport design. The ifnite 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 lfow-ifelds. The tail shock changes from a single to multiple-shock waveform from on-track to off-track. There is very few inlfuence 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.
      作者: 徐悦 宋万强
      Author: XU Yue SONG Wanqiang
      作者单位: 中国航空研究院 航空数值模拟技术研究应用中心,北京,100012
      刊 名: 航空科学技术
      年,卷(期): 2016, 27(7)
      分类号: V221.3
      机标分类号: TS9 TN6
      在线出版日期: 2016年8月12日