Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)
Yamaha Motor Co., Ltd.
Canon Inc.
TOUA Co. Ltd.
Tokyo Business Service Co. Ltd.
The transition characteristics were examined numerically on candidate shapes in order to design a natural laminar flow nose for a supersonic transport. Two types of deformation from a baseline shape were examined. One is sinusoidal type, and another is localized type. Not only parameters of geometry which define the deformation, but also the conditions of uniform flow were varied to obtain the largest effect of natural laminar flow. In results, the crossflow instability, which dominates the boundary-layer transition at the side area, was found to be suppressed from the small ratio of pressure gradients in azimuthal and axial directions at the side area. Moreover it was found that the relative location of bump in pressure distribution along leeward and windward rays is a key to yield small ratio of pressure gradient in azimuthal direction. The effect of natural laminar flow for sinusoidal deformation was confirmed experimentally. On the other hand, the localized deformation was found to be more effective in order to suppress increasing of total drag than the sinusoidal deformation.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
波状変形による超音速自然層流機首の設計
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