The addition of wedge-like fairings onto the side of missiles and space launch vehicles, to shield devices such as cameras and reaction jet nozzles, creates additional drag, particularly when in supersonic and hypersonic freestream flow. An experimental and computational study was performed to obtain aerodynamic data on simple representative configurations to test the accuracy of simple theories for the drag increment due to these types of fairings. A semi-empirical method to estimate drag on wedge-shaped projections is presented, which may be used by missile designers to provide predictions of the drag increment due to wedge-like fairings. The method is shown to be valid where the wedge width is much smaller than body diameter, and across the Mach number range 4–8.2 but is likely to be valid for higher Mach numbers. Drag coefficient is found to increase with increasing wedge angle and reducing wedge slenderness, although increasing slenderness tends to increase skin friction drag.

中文翻译：

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高超声速流中楔形整流罩阻力估计的简单方法

在导弹和太空运载火箭的侧面增加楔形整流罩，以屏蔽照相机和反应射流喷嘴等设备，会产生额外的阻力，特别是在超音速和高超音速自由流中。进行了一项实验和计算研究，以获得简单代表性配置的空气动力学数据，以测试由于这些类型的整流罩而导致的阻力增量的简单理论的准确性。提出了一种估计楔形投影阻力的半经验方法，导弹设计人员可以使用该方法来预测由于楔形整流罩引起的阻力增量。该方法在楔形宽度远小于主体直径的情况下有效，并且在马赫数范围 4-8.2 范围内有效，但可能对更高的马赫数有效。