@inproceedings{oai:jaxa.repo.nii.ac.jp:00037875,
 author = {山崎, 哲夫 and 内田, 隆志 and Yamazaki, Tetsuo and Uchida, Takashi},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Dec},
 note = {第2世代超音速輸送機の設計において巡航時の揚抗比を向上させることは最も重要な課題の一つである。この比は次世代SSTの経済性に影響を持つが、これを悪化させる幾つかの要因がある。翼とナセルの干渉はその一つである。翼下に4基のナセルをもつSST形状にオイラー方程式解法を適用したところ、その揚抗比は翼胴結合体にナセル1基分の4倍を加えた場合よりも高くなった。また、翼の圧力場のために、ナセル直前の流入マッハ数は主流マッハ数より低くなり、流れは傾く。このようなことから、翼とナセルの干渉を更に詳しく調べることが必要である。, In designing the second generation of Supersonic Transport (SST), the improvement of the lift to drag ratio at cruise condition is one of the most important subjects. This ratio affects the economic viability of the next SST, but there are some phenomena which degrade it. One of these is the wing-nacelle interference. An Euler method has been applied to a SST configuration which have four nacelles located under the aft wing. In this result the whole configuration has a higher inviscid lift to drag ratio than the sum of the wing-body configuration and four times of only one nacelle. And the inflow Mach number just upstream of a nacelle is less than the free stream Mach number and the flow is inclined, owing to the wing surface pressure. Therefore it is necessary to investigate the wing-nacelle interference in more detail., 資料番号: AA0004174038, レポート番号: NAL SP-27},
 pages = {261--265},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {超音速輸送機全機形状の数値解析},
 volume = {27},
 year = {1994}
}