In this review paper, low-speed computational work from NASA Langley Research Center in support of the Space Launch System (SLS) is discussed. This information includes both historical and present efforts with the Kestrel computational fluid dynamics solver. The low-speed aerodynamics of SLS is highly complex, and the analysis of the unsteady flowfield requires significant computational efforts. The SLS mission profile varies from the vehicle static on the launch pad through high-speed ascent. This study focuses on the prelaunch as well as liftoff and transition portions of the flight both in proximity to the launch tower and in isolation. High-alpha conditions, as large as 90 deg, result in a flowfield dominated by massive, large-scale flow separation and asymmetric vortices. High-fidelity solutions require an unsteady computational formulation to accurately capture the aerodynamics of the vehicle. A detailed discussion of the computational approach is presented, followed by key efforts to support the program, both historic and present, including information that has been either published previously or that has never before been published external to NASA.

在这篇综述论文中，讨论了 NASA 兰利研究中心支持太空发射系统 (SLS) 的低速计算工作。此信息包括 Kestrel 计算流体动力学求解器的历史和当前工作。 SLS的低速空气动力学非常复杂，非定常流场的分析需要大量的计算工作。 SLS 的任务概况从发射台上的车辆静态到高速上升不等。这项研究的重点是发射前以及飞行的升空和过渡部分，包括靠近发射塔和孤立的部分。高达 90 度的高α条件会导致流场以大量、大规模的流动分离和不对称涡流为主。高保真解决方案需要非稳态计算公式来准确捕获车辆的空气动力学特性。详细讨论了计算方法，然后介绍了支持该计划的关键努力，无论是历史上的还是现在的，包括以前发布过的信息或以前从未在 NASA 外部发布过的信息。