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Aerodynamic design of natural laminar flow supersonic aircraft wings
https://jaxa.repo.nii.ac.jp/records/41445
https://jaxa.repo.nii.ac.jp/records/41445b43d62f9-d974-4153-b4b7-57af42a3cf0b
名前 / ファイル | ライセンス | アクション |
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nalsp0049029.pdf (1.4 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aerodynamic design of natural laminar flow supersonic aircraft wings | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速航空機翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | NLF | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 自然層流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層安定解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速実験機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | L/D比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚力対抗力比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 逆設計法 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic aircraft wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | NLF | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | natural laminar flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer stability analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic experimental aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | L to D ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift to drag ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | inverse design method | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル | ||||||
その他のタイトル | 自然層流超音速航空機翼の空力設計 | |||||
著者 |
生越, 博景
× 生越, 博景× Ogoshi, Hirokage |
|||||
著者所属 | ||||||
川崎重工業 岐阜技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries LTD Gifu Technology Institute | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 49T, p. 203-209, 発行日 2000-12 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 航空宇宙技術研究所 17-19 Jan. 2000 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 超音速航空機の翼に対する自然層流(NLF)の空力設計を3次元CFD(計算流体力学)および境界層安定解析を用い行った。NLF翼設計に対して2つの主題がある。1つは航空宇宙技術研究所(NAL)の小型無人超音速実験機のL/D(揚力/抗力)比を改善することである。全抗力のほとんど半分に達するこの翼部の表面摩擦抗力を減少するため特に設計を行った。この目的のために3次元CFDソルバおよび3次元層流境界安定解析と2次元逆設計法を用い出来るだけ層流を維持するように設計した。もう1つは翼長方向の圧力分布を考慮してクロス流れの不安定性による遷移を遅らせるように簡単な後退翼を設計した。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Aerodynamic design of Natural Laminar Flow (NLF) for supersonic aircraft wings was conducted by using 3-D CFD 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/Drag) ratio. The 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. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0028638029 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-49T |