WEKO3
アイテム
{"_buckets": {"deposit": "bfe63130-f466-45ad-94bd-0547bb438c50"}, "_deposit": {"created_by": 1, "id": "35517", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "35517"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00035517", "sets": ["1890", "1909"]}, "author_link": ["422277", "422273", "422275", "422276", "422272", "422274"], "item_9_alternative_title_2": {"attribute_name": "その他のタイトル(英)", "attribute_value_mlt": [{"subitem_alternative_title": "Aerodynamic Characteristics of Conecylinder at Transonic Speeds"}]}, "item_9_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "1963-09", "bibliographicIssueDateType": "Issued"}, "bibliographicIssueNumber": "7", "bibliographicPageEnd": "648", "bibliographicPageStart": "631", "bibliographicVolumeNumber": "3", "bibliographic_titles": [{"bibliographic_title": "東京大学航空研究所集報"}]}]}, "item_9_description_16": {"attribute_name": "抄録", "attribute_value_mlt": [{"subitem_description": "sting-Type Balanceを使って遷音速におけるCone-Cylinderに働く3分力の測定を行なった実験結果を報告する.実験に使用したConeの半頂角は10°,15°,20°,25°および30°の5種である.小さな迎角の範囲では揚力は迎角に比例して増加し零迎角における揚力係数勾配はM=1の近傍でSlender Body Theoryのそれと大体一致する.模型の尖端周りのPitching-Moment係数は小迎角の範囲では,迎角に比例して増加するが,増加の割合はSlender Body Theoryのそれと比較してかなり小さい.零揚力における抵抗係数は半頂角20°および25°の模型に対してはCole, SolomonおよびWillmarthの実験結果[3]と良く一致している.しかし遷音速相似法則による抵抗係数の整理は良い結果を示さない.大きな半頂角の模型(25°および30°)に関しては揚力係数およびPitching-Moment係数がM=0.89の近傍でほとんど不連続的と考えられるような急激な減少を示した.一方抵抗係数の変化は連続的であった.Schlieren写真による流れ場の観察により,このような空力特性の急減は模型の肩における非対称剥離と衝撃波の位置の変化によるという結論に達した.", "subitem_description_type": "Abstract"}]}, "item_9_description_17": {"attribute_name": "抄録(英)", "attribute_value_mlt": [{"subitem_description": "Present paper gives the results of experimental investigation on the aerodynamic characteristics of the simple bodies at transonic speeds. Models used in the experiment are the cone-cylinders with semi-vertex angle of 10°, 15°, 20°, 25°and 30°, respectively. In the region of small angle of attack the lift-coefficient inceases proportionally to the increase of the incidence and, at zero angle of attack, the lift-curve slope near Mach number one shows fairly good agreement with that obtained by slender body theory. The drag data for models with semi-angle of 20°and 25°agree well with those obtained by Cole, Solomon and Willmarth [3], but the transonic similarity law does not lead to good arrangement of the pressure drag coefficients at zero angle of attack. For models with semi-angle of 25°and 30°and at small angle of attack the lift-coefficient and pitching-moment coefficient decrease abruptly near Mach number of 0.89. Observation of the flow field by schlieren method reveals that the abrupt decrease is caused by asymmetric separation of boundary layer near the shoulder of the cone and asymmetric growth of shock wave on the cylinder.", "subitem_description_type": "Other"}]}, "item_9_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: SA4148580000", "subitem_description_type": "Other"}]}, "item_9_publisher_8": {"attribute_name": "出版者", "attribute_value_mlt": [{"subitem_publisher": "東京大学航空研究所"}]}, "item_9_source_id_21": {"attribute_name": "ISSN", "attribute_value_mlt": [{"subitem_source_identifier": "0563-8097", "subitem_source_identifier_type": "ISSN"}]}, "item_9_source_id_24": {"attribute_name": "書誌レコードID", "attribute_value_mlt": [{"subitem_source_identifier": "AN00162214", "subitem_source_identifier_type": "NCID"}]}, "item_9_text_34": {"attribute_name": "メタデータ提供者", "attribute_value_mlt": [{"subitem_text_value": "メタデータ提供者: ISASNII"}]}, "item_9_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: 宇宙科学研究所"}]}, "item_9_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 6"}]}, "item_creator": {"attribute_name": "著者", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "河村, 龍馬"}], "nameIdentifiers": [{"nameIdentifier": "422272", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "辛島, 桂一"}], "nameIdentifiers": [{"nameIdentifier": "422273", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "関, 和市"}], "nameIdentifiers": [{"nameIdentifier": "422274", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "KAWAMURA, Ryuma", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "422275", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "KARASHIMA, Keiichi", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "422276", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "SEKI, Kazuichi", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "422277", "nameIdentifierScheme": "WEKO"}]}]}, "item_files": {"attribute_name": "ファイル情報", "attribute_type": "file", "attribute_value_mlt": [{"accessrole": "open_date", "date": [{"dateType": "Available", "dateValue": "2020-01-24"}], "displaytype": "detail", "download_preview_message": "", "file_order": 0, "filename": "SA4148580.pdf", "filesize": [{"value": "861.3 kB"}], "format": "application/pdf", "future_date_message": "", "is_thumbnail": false, "licensetype": "license_free", "mimetype": "application/pdf", "size": 861300.0, "url": {"label": "SA4148580.pdf", "url": "https://jaxa.repo.nii.ac.jp/record/35517/files/SA4148580.pdf"}, "version_id": "d596f739-e856-46d8-882b-c21a2865b54c"}]}, "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": "departmental bulletin paper", "resourceuri": "http://purl.org/coar/resource_type/c_6501"}]}, "item_title": "遷音速におけるCone-Cylinderの空力特性", "item_titles": {"attribute_name": "タイトル", "attribute_value_mlt": [{"subitem_title": "遷音速におけるCone-Cylinderの空力特性"}]}, "item_type_id": "9", "owner": "1", "path": ["1890", "1909"], "permalink_uri": "https://jaxa.repo.nii.ac.jp/records/35517", "pubdate": {"attribute_name": "公開日", "attribute_value": "2015-03-26"}, "publish_date": "2015-03-26", "publish_status": "0", "recid": "35517", "relation": {}, "relation_version_is_last": true, "title": ["遷音速におけるCone-Cylinderの空力特性"], "weko_shared_id": -1}
遷音速におけるCone-Cylinderの空力特性
https://jaxa.repo.nii.ac.jp/records/35517
https://jaxa.repo.nii.ac.jp/records/35517fb09239f-00c1-4511-86a7-86bcae3dea02
名前 / ファイル | ライセンス | アクション |
---|---|---|
SA4148580.pdf (861.3 kB)
|
|
Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 遷音速におけるCone-Cylinderの空力特性 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Aerodynamic Characteristics of Conecylinder at Transonic Speeds | |||||
著者 |
河村, 龍馬
× 河村, 龍馬× 辛島, 桂一× 関, 和市× KAWAMURA, Ryuma× KARASHIMA, Keiichi× SEKI, Kazuichi |
|||||
出版者 | ||||||
出版者 | 東京大学航空研究所 | |||||
書誌情報 |
東京大学航空研究所集報 巻 3, 号 7, p. 631-648, 発行日 1963-09 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | sting-Type Balanceを使って遷音速におけるCone-Cylinderに働く3分力の測定を行なった実験結果を報告する.実験に使用したConeの半頂角は10°,15°,20°,25°および30°の5種である.小さな迎角の範囲では揚力は迎角に比例して増加し零迎角における揚力係数勾配はM=1の近傍でSlender Body Theoryのそれと大体一致する.模型の尖端周りのPitching-Moment係数は小迎角の範囲では,迎角に比例して増加するが,増加の割合はSlender Body Theoryのそれと比較してかなり小さい.零揚力における抵抗係数は半頂角20°および25°の模型に対してはCole, SolomonおよびWillmarthの実験結果[3]と良く一致している.しかし遷音速相似法則による抵抗係数の整理は良い結果を示さない.大きな半頂角の模型(25°および30°)に関しては揚力係数およびPitching-Moment係数がM=0.89の近傍でほとんど不連続的と考えられるような急激な減少を示した.一方抵抗係数の変化は連続的であった.Schlieren写真による流れ場の観察により,このような空力特性の急減は模型の肩における非対称剥離と衝撃波の位置の変化によるという結論に達した. | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Present paper gives the results of experimental investigation on the aerodynamic characteristics of the simple bodies at transonic speeds. Models used in the experiment are the cone-cylinders with semi-vertex angle of 10°, 15°, 20°, 25°and 30°, respectively. In the region of small angle of attack the lift-coefficient inceases proportionally to the increase of the incidence and, at zero angle of attack, the lift-curve slope near Mach number one shows fairly good agreement with that obtained by slender body theory. The drag data for models with semi-angle of 20°and 25°agree well with those obtained by Cole, Solomon and Willmarth [3], but the transonic similarity law does not lead to good arrangement of the pressure drag coefficients at zero angle of attack. For models with semi-angle of 25°and 30°and at small angle of attack the lift-coefficient and pitching-moment coefficient decrease abruptly near Mach number of 0.89. Observation of the flow field by schlieren method reveals that the abrupt decrease is caused by asymmetric separation of boundary layer near the shoulder of the cone and asymmetric growth of shock wave on the cylinder. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0563-8097 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00162214 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA4148580000 |