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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >Assessment of CFD Estimation of Aerodynamic Characteristics of Basic Reusable Rocket Configurations
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Assessment of CFD Estimation of Aerodynamic Characteristics of Basic Reusable Rocket Configurations

机译：基本可重复使用火箭构型气动特性的CFD估算评估

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Flow-fields around the basic SSTO-rocket configurations are numerically simulated by the Reynolds-averaged Nav-ier-Stokes (RANS) computations. Simulations of the Apollo-like configuration is first carried out, where the results are compared with NASA experiments and the prediction ability of the RANS simulation is discussed. The angle of attack of the freestream ranges from 0° to 180° and the freestream Mach number ranges from 0.7 to 2.0. Computed aerodynamic coefficients for the Apollo-like configuration agree well with the experiments under a wide range of flow conditions. The flow simulations around the slender Apollo-type configuration are carried out next and the results are compared with the experiments. Computed aerodynamic coefficients also agree well with the experiments. Flow-fields are dominated by the three-dimensional massively separated flow, which should be captured for accurate aerodynamic prediction. Grid refinement effects on the computed aerodynamic coefficients are investigated comprehensively.
机译：基本的SSTO火箭构型周围的流场通过雷诺平均Nav-ier-Stokes（RANS）计算进行数值模拟。首先进行类似阿波罗的配置的仿真，然后将结果与NASA实验进行比较，并讨论了RANS仿真的预测能力。自由流的攻角范围为0°至180°，自由马赫数的范围为0.7至2.0。计算出的类似阿波罗飞机的空气动力学系数与各种流动条件下的实验吻合得很好。接下来围绕细长的Apollo型构造进行流动模拟，并将结果与​​实验进行比较。计算出的空气动力学系数也与实验吻合得很好。流场主要由三维分离的三维流控制，应对其进行捕获以进行准确的空气动力学预测。全面研究了网格细化对计算出的空气动力系数的影响。

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