{"_buckets": {"deposit": "4f39fd21-a12b-4a24-9b5e-0a44180720c3"}, "_deposit": {"created_by": 1, "id": "6593", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "6593"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00006593", "sets": ["1365", "1891"]}, "author_link": ["33742", "33738", "33735", "33734", "33739", "33736", "33743", "33741", "33740", "33737"], "item_5_alternative_title_2": {"attribute_name": "その他のタイトル（英）", "attribute_value_mlt": [{"subitem_alternative_title": "Boundary-layer transition measurements of SST experimental airplane at ONERA-S2MA"}]}, "item_5_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "2004-03-25", "bibliographicIssueDateType": "Issued"}, "bibliographicPageEnd": "29", "bibliographicPageStart": "23", "bibliographicVolumeNumber": "JAXA-SP-03-003", "bibliographic_titles": [{"bibliographic_title": "宇宙航空研究開発機構特別資料: 第66回　風洞研究会議論文集"}, {"bibliographic_title": "JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 66th Meeting", "bibliographic_titleLang": "en"}]}]}, "item_5_description_16": {"attribute_name": "抄録", "attribute_value_mlt": [{"subitem_description": "摩擦抵抗を軽減した自然層流翼を基本概念として設計されたSSTロケット実験機の実証飛行試験に先立ち、遷移予測コードの検証用データベースを構築するため、ONERA回流式大型超音速風洞S2MAにおいて全機模型の遷移過程を計測した。本風洞では国内の風洞で実現されない飛行条件に近い高レイノルズ数が達成され、またマッハ数、風洞総圧、迎角および横滑り角などが制御可能である。多点熱膜流速計から決定された遷移点は、赤外線画像の計測結果とよく一致し、レイノルズ数の増加に伴って上流へ移動することが確かめられた。前縁から遷移点までの距離に基づく遷移レイノルズ数は、マッハ数を2に固定した場合、主流レイノルズ数には依存しなかった。一方、迎角依存性は、内翼と外翼で異なっていた。内翼では、設計迎角において最も遷移点が下流に移動した。それに対し外翼では、5度までの範囲で迎角が大きいほど遷移が遅くなった。これらの迎角依存性を導く遷移機構は、圧力分布から理解可能である。また、主流の総圧変動はマッハ数によって0.1〜0.35％と大きく変化したが、風洞総圧には依存しなかった。", "subitem_description_type": "Abstract"}]}, "item_5_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA0047428004", "subitem_description_type": "Other"}]}, "item_5_description_33": {"attribute_name": "レポート番号", 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