鈍頭半円錐物体の超音速空力特性とその背面剥離の可視化実験

Material type: 文書・図像類

Author: 河本, 巖ほか

Publisher: 航空宇宙技術研究所

Publication date: 1979-09

Material Format: Digital

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Note (General)：: This paper presents the aerodynamic characteristics of some blunt half-cones with and without fins which have been considered typical configurations o...

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Material Type: 文書・図像類
Title: 鈍頭半円錐物体の超音速空力特性とその背面剥離の可視化実験
Author/Editor: 河本, 巖
清水, 福寿
外立, 政隆
野田, 順一
関根, 英夫
石田, 清道
KAWAMOTO, Iwao
SHIMIZU, Fukuju
HASHIDATE, Masataka
NODA, Jun-ichi
SEKINE, Hideo
ISHIDA, Kiyomichi
Author Heading: 河本, 巖
清水, 福寿
外立, 政隆
野田, 順一
関根, 英夫
石田, 清道
KAWAMOTO, Iwao
SHIMIZU, Fukuju
HASHIDATE, Masataka
NODA, Jun-ichi
SEKINE, Hideo
ISHIDA, Kiyomichi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1979-09
Publication Date (W3CDTF): 1979-09
Alternative Title: Aerodynamic and Flow-Visualization Studies of Half-blunt Cones at Supersonic Speeds
Periodical title: 航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
No. or year of volume/issue: 393
Volume: 393
Pages: 42-
ISSN (Periodical Title): ISSN : 0452-2982
Text Language Code: jpn
Target Audience: 一般
Note (General): This paper presents the aerodynamic characteristics of some blunt half-cones with and without fins which have been considered typical configurations of lifting recovering-bodies,and the flow visualizations of leeward separation at angles of attack.The wind tunnel force tests were conducted over the Mach number range 1.5 to 3.0 and for angles of attack from -25° to 25°.The experimental results show that the aerodynamic hysteresis due to lee-surface separation was not observed and,CN and Cm against α were well predicted by slender body approximation better than by Newtonian approximation.The flow-visualizations of lee-surface separation were also conducted at low supersonic speeds.Visualization techniques consisted of the schlieren,oil flow and vapor screen methods.In the vapor screen photographs,two flow patterns over the leeside of a half-cone were observed according to attack angle.The first,at a 10° attack angle,had only a pair of vortex similar to incompressible flow cases.The second,at a 20° atthad a plane shock wave connected with a pair of vortexes.The lee-surface flow patterns were schematically depicted from these visualized pictures.
資料番号: NALTM0393000
レポート番号: NAL TM-393
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43976&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43976&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ