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首页> 外文期刊>Journal of Spacecraft and Rockets >Effect of Computational Method on Discrete Roughness Correlations for Shuttle Orbiter
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Effect of Computational Method on Discrete Roughness Correlations for Shuttle Orbiter

机译：计算方法对穿梭轨道器离散粗糙度相关性的影响

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摘要

A reanalysis of discrete roughness boundary-layer transition data using a consistent computational method for comparison to other published results has been completed. The primary objective of this effort was to investigate the influence of the computational approach on the resulting transition correlation. The experimental results were previously obtained on Space Shuttle Orbiter models in the NASA Langley Research Center 20-Inch Mach 6 Air Tunnel. The phosphor thermography system was used to monitor the status of the boundary layer via global heat-transfer images of the orbiter windward surface. The existing roughness transition database included a variation in the size and location of discrete roughness trips along the centerline of 0.0075-scale models at an angle of attack of 40 deg. Various correlative approaches were attempted, with the roughness transition correlations based on edge properties providing the most reliable results. When a consistent computational method is used to compute edge conditions, transition data sets for different moderately blunt configurations at several angles of attack are shown to collapse to a well-behaved correlation. The shuttle experimental dataset presented herein, therefore, can be used to calibrate the preferred computational method of the end user for use in the future designs of the next-generation space access vehicles.
机译：使用一致的计算方法对离散粗糙度边界层过渡数据的重新分析已完成，可以与其他已发表的结果进行比较。这项工作的主要目的是研究计算方法对所得过渡相关性的影响。实验结果先前是在NASA Langley研究中心20英寸马赫6空中隧道的航天飞机轨道器模型上获得的。荧光粉热成像系统用于通过轨道飞行器迎风面的整体传热图像来监测边界层的状态。现有的粗糙度过渡数据库包括沿0.0075比例模型中心线以40度攻角的离散粗糙度行程的大小和位置的变化。尝试了各种相关方法，其中基于边缘特性的粗糙度过渡相关性提供了最可靠的结果。当使用一致的计算方法来计算边缘条件时，在几个攻角下用于不同中等钝性配置的过渡数据集会崩溃，表现出良好的相关性。因此，本文介绍的航天飞机实验数据集可用于校准最终用户的首选计算方法，以用于下一代太空通道飞行器的未来设计中。

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