MEASUREMENT OF AERODYNAMIC CHARACTERISTICS OF A HANG-GLIDER-WING BY GROUND RUN TESTS USING A TEST VEHICLE

Material type: 文書・図像類

Author: 穂積, 弘毅ほか

Publisher: 航空宇宙技術研究所

Publication date: 1987-11

Material Format: Digital

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Note (General)：: In order to investigate longitudinal force and moment characteristics of a hang-glider-wing, ground run tests were conducted using a test vehicle. A h...

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Material Type: 文書・図像類
Title: MEASUREMENT OF AERODYNAMIC CHARACTERISTICS OF A HANG-GLIDER-WING BY GROUND RUN TESTS USING A TEST VEHICLE
Author/Editor: 穂積, 弘毅
古茂田, 真幸
小野, 孝次
塚野, 雄吉
HOZUMI, Koki
KOMODA, Masaki
ONO, Takatsugu
TSUKANO, Yukichi
Author Heading: 穂積, 弘毅
古茂田, 真幸
小野, 孝次
塚野, 雄吉
HOZUMI, Koki
KOMODA, Masaki
ONO, Takatsugu
TSUKANO, Yukichi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1987-11
Publication Date (W3CDTF): 1987-11
Alternative Title: 走行実験によるハンググライダ翼の空力特性について
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-953
No. or year of volume/issue: 953
Volume: 953
Pages: 23-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): In order to investigate longitudinal force and moment characteristics of a hang-glider-wing, ground run tests were conducted using a test vehicle. A hang-glider-wing was installed on a test vehicle using a six-components-balance for wind tunnel use. Aerodynamic force and moment were measrued during the vehicle run at various constant speeds. Geometrical twist distribution along the wing span was recorded as well. Measured force and moment data were corrected for possible ground effect and upwash effect due to movement of the vehicle. The lift curve slope was about 23％ smaller than that predicted by theory for a rigid wing of the same geometry. An abrupt increase in the pitching moment was measured as CL decreased from positive to negative. These particular features indicate that aeroelastic deformations affect the aerodynamic characteristics of hang-gliders and/or motor-hang-gliders are mandatory for their flight safety. Using the Moriya method, aeroelastic camber variations at typical spanwise stations were estimated for each combination of dynamic pressure and section angle of attack. Applying the Weissinger method, lift and pitching moment characteristics were analyzed twist distributions. By comparing these analyses with the measured data, geometrical deformations of the flexible wing were elucidated.
資料番号: NALTR0953000
レポート番号: NAL TR-953
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