日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
論文
胴体先端形状修正による翼胴型超音速複葉翼機のソニックブーム低減化
大久保 正幸豊田 篤山下 博小川 俊広大林 茂清水 克也鈴木 角栄松田 淳佐宗 章弘
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2011 年 59 巻 688 号 p. 119-125

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To examine the possibility of sonic boom mitigation by the supersonic biplane with a fuselage, two kinds of wing-fuselage models for the ballistic range experiment were designed by using CFD simulations. One was the low-boom model with a blunt nose and the other was the high-boom model with a spike nose. From the CFD result, the near-field pressure strength from the low-boom model becomes 70% of that of the high-boom model. The far-field pressure peak of the low-boom model becomes 85% of that of the high-boom model. To verify the near-field pressure signature calculated by CFD, the experimental model using the supersonic biplane with a finite-thickness leading edge was designed and launched with the ballistic range. As a result, the reliability of the CFD result was confirmed.

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© 2011 The Japan Society for Aeronautical and Space Sciences
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