Aerodynamic design of Natural Laminar Flow supersonic aircraft wings

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SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 東京 日本

SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan

Aerodynamic design of Natural Laminar Flow (NLF) for supersonic aircraft wings was conducted by using 3-D CFD (Computational Fluid Dynamics) analysis and boundary layer stability analysis. There are two main subjects for NLF wing design. One is that the wing of the sub-scaled unmanned supersonic experimental aircraft of National Aerospace Laboratory (NAL) was designed to improve the L/D (Lift to Drag) ratio. This wing sections were designed especially to reduce skin friction drag which amounts to nearly half of the total drag. For this purpose, we designed the wing sections to remain laminar flow as far as possible using 3-D CFD solver and 3-D laminar boundary layer stability analysis code and 2-D inverse design method. The other is that the simple sweep-back wing was designed to delay a transition due to cross flow instability in consideration of spanwise pressure distribution. (This design concept of NLF is patented.)

資料番号: AA0063609046

レポート番号: JAXA-SP-06-029E

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詳細情報 詳細情報について

  • CRID
    1050292561218607744
  • NII論文ID
    120006829188
  • NII書誌ID
    AA11984031
  • ISSN
    1349113X
  • Web Site
    http://id.nii.ac.jp/1696/00005771/
  • 本文言語コード
    en
  • 資料種別
    conference paper
  • データソース種別
    • IRDB
    • CiNii Articles

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