{"created":"2023-06-20T15:10:05.440307+00:00","id":39682,"links":{},"metadata":{"_buckets":{"deposit":"c8cb3475-e511-4190-bdf4-3f2d1338ad93"},"_deposit":{"created_by":1,"id":"39682","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39682"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039682","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["443867","443873","443874","443869","443872","443870","443866","443868","443871","443875"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effect of film cooling/regenerative cooling on scramjet engine performances"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"14","bibliographicPageStart":"1","bibliographicVolumeNumber":"1242","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"フィルム冷却を用いたスクラムジェットエンジンの性能を予測するために、新しいフィルム冷却モデルを提案した。フィルム冷却のモデル化は、フィルム冷却剤の噴射スロット近傍を記述するのに圧縮性混合層の実験結果を用い、噴射スロットから十分に下流の領域を記述するのに乱流境界層の解析結果を用いて行った。実験結果との比較によって本モデルの有効性を確認した後、本モデルをスクラムジェットエンジンの準1次元シミュレーションプログラムに組み込んで性能計算を行った。シミュレーションは冷却システムの異なる3種類(フィルム冷却、再生冷却、およびフィルム/再生併用冷却)のエンジンシステムについて行い、それらの性能を比較検討した。フィルム冷却と再生冷却を併用した場合には、高飛行マッハ数領域においても化学量論混合比燃料流量をわずかに上回る程度の冷却剤流量ですみ、比推力および燃料供給圧力の点から見て最も高い性能を示した。これは併用冷却によってフィルム冷却剤の体積流量が増加し、同時に、主流とフィルム冷却剤間の速度差が小さくなるために生じた。さらに、併用冷却ではエンジン壁の過剰冷却領域が発生しなかった。フィルム冷却と再生冷却の併用は燃料供給システムの点から見ても有効であり、燃料供給システムから発生するタービン排ガスは効果的なフィルム冷却剤になることが分かった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Film cooling was modeled to allow performance prediction of scramjet engine design. The model was based on experimental results of compressible mixing layers for the vicinity of the injection slot, and on analytical results of the turbulent boundary layer in the region far from the slot. The film cooling model was integrated to a quasi one-dimensional scramjet performance prediction model. In the engine employing a combination of film cooling and regenerative cooling, coolant flow rate of the engine slightly exceeded the stoichiometric flow rate, even at high flight Mach numbers, and had the best specific impulse and system pressure performances. These advantages were achieved by increasing the volume flow rate and decreasing the velocity difference between the main flow and the coolant, both due to an increase in the film coolant temperature. The effective cooling system with a combination of film cooling and regenerative cooling was also advantageous in that excess cooling of the engine wall could be avoided. The combination of film cooling and regenerative cooling was also effective from the viewpoint of the propellant feed system. The turbine exhaust gas was suitable for the coolant of film cooling.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000102000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL TR-1242","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"小野, 文衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"苅田, 丈士"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"升谷, 五郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"斎藤, 俊仁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"若松, 義男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ono, Fumiei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanda, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Masuya, Goro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saito, Toshihito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Wakamatsu, Yoshio","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-27"}],"displaytype":"detail","filename":"naltr01242.pdf","filesize":[{"value":"1.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01242.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39682/files/naltr01242.pdf"},"version_id":"f1e0430b-6e0c-4e30-8b9e-dd3e3b021518"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"スクラムジェットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"フィルム冷却","subitem_subject_scheme":"Other"},{"subitem_subject":"再生冷却","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"混合層","subitem_subject_scheme":"Other"},{"subitem_subject":"乱流境界層","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料供給システム","subitem_subject_scheme":"Other"},{"subitem_subject":"ガス発生機サイクル","subitem_subject_scheme":"Other"},{"subitem_subject":"性能計算","subitem_subject_scheme":"Other"},{"subitem_subject":"シミュレーションプログラム","subitem_subject_scheme":"Other"},{"subitem_subject":"化学量論混合比","subitem_subject_scheme":"Other"},{"subitem_subject":"比推力","subitem_subject_scheme":"Other"},{"subitem_subject":"冷却効率","subitem_subject_scheme":"Other"},{"subitem_subject":"冷却モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"scramjet engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"film cooling","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"regenerative heat cooling","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mixing layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"turbulent boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"propellant feed system","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"gas generator cycle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"performance calculation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"simulation program","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stoichiometric mixture ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"specific thrust","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cooling efficiency","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cooling model","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"フィルム冷却を用いたスクラムジェットエンジンの性能計算","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"フィルム冷却を用いたスクラムジェットエンジンの性能計算"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"39682","relation_version_is_last":true,"title":["フィルム冷却を用いたスクラムジェットエンジンの性能計算"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:19:45.367451+00:00"}