{"created":"2023-06-20T14:35:37.308631+00:00","id":1875,"links":{},"metadata":{"_buckets":{"deposit":"feb1445f-3cf1-4245-8a87-ac0f07bc9dbf"},"_deposit":{"created_by":1,"id":"1875","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"1875"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00001875","sets":["1887:1893","9:10:39:50"]},"author_link":["476604","476594","476607","476599","476603","476600","476601","476597","476595","476605","476598","476606","476602","476596"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Deviation in Standard Model Force Measurements in JAXA 1.27m Hypersonic Wind Tunnel"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2016-11-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"15","bibliographicPageStart":"1","bibliographicVolumeNumber":"JAXA-RR-16-004","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"過去に行われたJAXA 1.27m 極超音速風洞気流較正試験結果におけるMach数の平均値からのずれを再評価したところ、現状のデータ処理で用いられている振動励起エネルギーに関する平衡実在気体モデルに基づいて求められるMach 数と比べ完全気体モデルに基づいた処理の方がむしろバラつきの小さいことが判明した。そこでこの風洞のノズル流における振動励起緩和時間を推定したところ、ノズルスロート下流のある点より振動励起が保たれたままいわゆる凍結流となることが想定されたが、これは平衡実在気体モデルと比べ完全気体モデルの方が現実により近いことを支持する結果であった。また、一連の標準模型試験を実施することで提議されたもう一つの課題は、複数の試験キャンペーン間におけるモニター用ピトー圧比平均値及び空力特性におけるバラつきである。ピトー圧比計測結果の解析により、現状一定値として扱っていた一様流Mach 数は試験キャンペーン毎に変化している可能性が確認された。これら二つの問題が空力計測精度に及ぼす影響を評価する目的で、2002年から2016年にわたり行われたHB2標準模型6分力試験及びHRV カプセル形状模型6分力試験結果を用いて再評価した。その結果、まず現行の平衡実在気体モデルによる処理と比べ完全気体モデルを基にした処理により空力係数における再現性バラつきを低減させる可能性を示すことができた。また、試験キャンペーン間で変動していると考えられるピトー圧比を動圧推定に活用することによって試験キャンペーン間で見られていた空力係数における再現性バラつきをさらに低減させる可能性が示された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Re-examination of free stream Mach number calibration data obtained in JAXA 1.27m hypersonic wind tunnel suggests that the perfect gas assumption during nozzle expansion process results in less Mach number deviation throughout the test core region of the tunnel than the assumption of ‘real gas’ in equilibrium with respect to vibrational excitation which has been adopted in the facility. Vibrational relaxation time was then estimated so large that the vibrational energy excitation should effectively be frozen at a point downstream of the throat under typical operating conditions of the tunnel, which supports the validity of the perfect gas assumption in the nozzle flow estimation. Another problem posed by a series of standard model tests is unexpectedly large scatter in the monitored pitot pressure measurements between test campaigns. Analysis in the scatter of pitot pressure measurements suggests that the free stream Mach number which has been assumed constant could actually differs by the test campaign. Consequences of the above aspects to the force measurements are also evaluated by looking up results of HB2 standard model tests and of HRV capsule configuration tests conducted during a period from the year of 2002 to 2016. It suggests that scatters in force measurement could be reduced by adopting perfect gas assumption instead of the real gas equilibrium model, and also shows a possibility of further reduction in the data scatter observed between test campaigns by correcting free stream Mach number obtained only from the nozzle calibration tests by the monitoring pitot pressure measurements in each test blows.","subitem_description_type":"Other"}]},"item_3_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_3_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA1630025000","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: JAXA-RR-16-004","subitem_description_type":"Other"}]},"item_3_identifier_registration":{"attribute_name":"ID登録","attribute_value_mlt":[{"subitem_identifier_reg_text":"10.20637/JAXA-RR-16-004/0001","subitem_identifier_reg_type":"JaLC"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構(JAXA)"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構航空技術部門空力技術研究ユニット(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門空力技術研究ユニット(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門空力技術研究ユニット(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門空力技術研究ユニット(JAXA)"},{"subitem_text_value":"航空宇宙技術振興財団"},{"subitem_text_value":"航空宇宙技術振興財団"},{"subitem_text_value":"航空宇宙技術振興財団"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Aerodynamics Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Aerodynamics Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Aerodynamics Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Aerodynamics Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Japan AeroSpace Technology Foundation"},{"subitem_text_language":"en","subitem_text_value":"Japan AeroSpace Technology Foundation"},{"subitem_text_language":"en","subitem_text_value":"Japan AeroSpace Technology Foundation"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"藤井, 啓介"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"津田, 尚一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小山, 忠勇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高間, 良樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中川, 宗敬"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"板橋, 幸広"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中村, 晃祥"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujii, Keisuke","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsuda, Shoichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Koyama, Tadao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takama, Yoshiki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakagawa, Muneyoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Itabashi, Yukihiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakamura, Akiyoshi","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":"2020-01-31"}],"displaytype":"detail","filename":"AA1630025000.pdf","filesize":[{"value":"6.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"AA1630025000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/1875/files/AA1630025000.pdf"},"version_id":"3ad0c490-6482-4353-aac1-f127d5bdc10e"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Hypersonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"deviation in Mach number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic force measurement","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":"標準模型6分力試験結果を用いたJAXA1.27m極超音速風洞におけるデータバラつきに関する再評価","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"標準模型6分力試験結果を用いたJAXA1.27m極超音速風洞におけるデータバラつきに関する再評価"}]},"item_type_id":"3","owner":"1","path":["50","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2016-11-07"},"publish_date":"2016-11-07","publish_status":"0","recid":"1875","relation_version_is_last":true,"title":["標準模型6分力試験結果を用いたJAXA1.27m極超音速風洞におけるデータバラつきに関する再評価"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:37:37.278645+00:00"}