典型声爆研究模型近场预测统计量化分析评估

Quantitative Statistical Analysis of Near Field Sonic Boom Prediction on Typical Research Models

声爆预测是超声速民机设计的关键技术。排除认知不确定性因素外,近场声爆预测能力的成熟度主要取决于所采用的计算流体力学(CFD)求解方法捕捉激波间断的能力。以共用研究模型旋成体和三角翼作为研究对象,选取典型截面声爆信号过压峰值强度和位置为系统响应量,开展了初步的不确定度量化分析评估。结果表明,当前对简单构型的预测还不够准确,声爆信号近场预测能力的成熟度还有待进一步提高。需要进一步发展高可信度声爆预测方法,准确捕捉飞机近场空间脱体压力;针对所关注的系统响应量,开展更加具体的不确定度量化评估分析研究。

Sonic boom prediction is addressed as a key issue in supersonic civil aircraft design.Excluding epistemic uncertainty,the maturity of near-filed sonic boom predictive capability mainly depends on the capability of computational fluid dynamics(CFD)methods adapted to capture shock wave discontinuities.A statistical analysis is presented for an axisymmetric body(seeb-ALR)and simple delta wing body(DWB),focusing on the shock strength and locations,which are set in terms of system response quantities(SRQs)for preliminary uncertainty quantification estimation.Overall,the maturity of near-filed sonic boom predictive capability needs to be further improved,as it is not accurate enough for a simple configuration.It is necessary to develop highly credible prediction methods that can accurately describe near-field sonic boom signatures so as to capturing off-body pressure.Research focus should not only be on overpressure strength of nose shock,tail shock,wing leading edge shock,but also on the shock positions.More specific uncertainty quantification analysis needs to be further conducted for SRQs of interest.