超音速旅客機の後端ブーム低減効果を得るためのノズル形状及び噴流に関する実験と数値解析

DOI Web Site 参考文献4件
  • 赤塚 純一
    連絡先著者（Corresponding author）：akatsuka@chofu.jaxa.jp 国立研究開発法人宇宙航空研究開発機構
  • 小幡 秀幸
    東京農工大学大学院 現 株式会社小松製作所
  • 三木 肇
    国立研究開発法人宇宙航空研究開発機構
  • 上野 篤史
    国立研究開発法人宇宙航空研究開発機構
  • 渡辺 安
    国立研究開発法人宇宙航空研究開発機構

書誌事項

タイトル別名
  • Experimental and Numerical Investigation on Nozzle Exit Shape and Plume for Aft-Boom Mitigation of Supersonic Transport

抄録

<p>This paper describes effects of nozzle geometry and a jet plume on the near-field signature and the thrust performance to explore concepts of aft-boom mitigation for future supersonic transport. Numerical analyses of four kinds of convergent-divergent nozzles were conducted to investigate the sensitivity of the near-field signature and the thrust. The results showed that reducing expansion region at the boat-tail is important to reduce both the peak pressure of near-field signature and the nacelle drag. A nozzle shape, which has an inclined exit shape without a boat-tail portion at lower side, demonstrated a good potential to reduce aft-boom. Supersonic wind tunnel tests using a jet with high-pressure air were also performed to validate the numerical analyses and the results showed good agreement with numerical analyses. </p>

収録刊行物

参考文献 (4)*注記

もっと見る

キーワード

詳細情報 詳細情報について

問題の指摘

ページトップへ