This paper presents the results of turbulent flow simulations prepared for the Third AIAA Sonic Boom Prediction Workshop. Solutions were prepared for two geometries that exhibited shock–plume interaction features: the NASA biconvex shock–plume interaction wind-tunnel model, and the NASA C608 low-boom concept aircraft. The unstructured, finite volume Navier–Stokes solver UNS3D was used to predict the turbulent near-field flow with Menter’s $\kappa –\omega$ shear stress transport turbulence model. Four solver setups with different combinations of the flux function, gradient reconstruction, and slope limiter were applied to each geometry. UNS3D predictions were compared against a grid-specific ensemble dataset created using workshop participant submissions and experimental data when available. Predictions of the biconvex geometry were found to be in good agreement with both the experimental and ensemble datasets. The weighted least-squares with QR decomposition (LSQR) gradient reconstruction approach was only successful for the biconvex geometry, with no converged cases being achieved on C608 grids. The Dervieux limiter, used only to aid simulations on the C608 using weighted LSQR, was observed to be too dissipative to be of practical use. Near-field predictions of the C608 geometry using Green–Gauss gradient reconstruction and a modified Venkatakrishnan limiter were found to correlate well with the ensemble data. The perceived level of the resulting sonic boom carpet was 1.5 dB quieter along the first 20 deg of the carpet than the ensemble mean, and it peaked at an azimuth angle of 30 deg with a value of 76.1 dB. A study of the undertrack near-field pressure signature revealed the components of the predicted signatures responsible for the variances observed in the sonic boom carpet.

本文介绍了为第三届 AIAA 音爆预测研讨会准备的湍流模拟结果。为表现出冲击-羽流相互作用特征的两种几何结构准备了解决方案：NASA 双凸面冲击-羽流相互作用风洞模型和 NASA C608 低臂概念飞机。非结构化、有限体积 Navier-Stokes 求解器 UNS3D 用于通过 Menter 预测湍流近场流$\kappa \mathrm{——}\omega$剪应力输运湍流模型。四个求解器设置与通量函数、梯度重建和斜率限制器的不同组合应用于每个几何。将 UNS3D 预测与使用研讨会参与者提交的数据和可用的实验数据创建的特定于网格的集合数据集进行比较。发现双凸几何的预测与实验数据集和集合数据集都非常吻合。带 QR 分解 (LSQR) 梯度重建方法的加权最小二乘法仅适用于双凸几何，在 C608 网格上没有实现收敛情况。Dervieux 限制器仅用于辅助使用加权 LSQR 对 C608 进行模拟，但被观察到耗散太大而无法实际使用。发现使用格林-高斯梯度重建和修改的 Venkatakrishnan 限制器对 C608 几何形状的近场预测与集合数据相关性很好。由此产生的音爆地毯的感知水平沿着地毯的前 20 度比整体平均值低 1.5 分贝，并且在 30 度的方位角达到峰值，值为 76.1 分贝。对轨道下近场压力特征的研究揭示了导致音爆地毯中观察到的变化的预测特征的组成部分。它在 30 度的方位角达到峰值，值为 76.1 dB。对轨道下近场压力特征的研究揭示了导致音爆地毯中观察到的变化的预测特征的组成部分。它在 30 度的方位角达到峰值，值为 76.1 dB。对轨道下近场压力特征的研究揭示了导致音爆地毯中观察到的变化的预测特征的组成部分。