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

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  • Sonic Boom Mitigation by Shaping the Nose of Supersonic Biplane
  • ドウタイ センタン ケイジョウ シュウセイ ニ ヨル ヨク ドウガタ チョウオンソク フクヨウヨクキ ノ ソニックブーム テイゲンカ

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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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