A numerical investigation of transonic flow around a mechanically deployable entry system being considered for a robotic mission to Venus has been performed, and preliminary results are reported. The flow around a conceptual representation of the vehicle geometry was simulated at discrete points along a ballistic trajectory using Detached Eddy Simulation (DES). The trajectory points selected span the low supersonic to transonic regimes with freestream Mach numbers from 1:5 to 0:8, and freestream Reynolds numbers (based on diameter) between 2:09 x 10(exp 6) and 2:93 x 10(exp 6). Additionally, the Mach 0:8 case was simulated at angles of attack between 0 and 5 . Static aerodynamic coefficients obtained from the data show qualitative agreement with data from 70deg sphere-cone wind tunnel tests performed for the Viking program. Finally, the effect of choices of models and numerical algorithms is addressed by comparing the DES results to those using a Reynolds Averaged Navier-Stokes (RANS) model, as well as to results using a more dissipative numerical scheme.
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机译：已经对围绕可机械展开的进入系统进行的跨音速流动进行了数值研究，该系统正在考虑执行向金星的机器人任务，并报告了初步结果。使用Dedched Eddy Simulation（DES）在沿弹道的离散点模拟了车辆几何概念表示周围的流动。选择的轨迹点跨越低速超声到跨音速状态，自由马赫数从1：5到0：8，自由雷诺数（基于直径）在2:09 x 10（exp 6）到2:93 x 10（实验6）。此外，以0到5的迎角模拟了0：8马赫的情况。从数据中获得的静态空气动力学系数与针对维京计划进行的70度球形圆锥风洞测试的数据在质量上具有一致性。最后，通过将DES结果与使用雷诺平均Navier-Stokes（RANS）模型的结果以及使用耗散性更高的数字方案的结果进行比较，可以解决模型和数值算法选择的影响。
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