JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
64671000.pdf3.23 MB
title二次元翼型試験における側壁境界層吸取り効果について
Other TitleEffects of Sidewall Boundary Layer Suction in Two dimensional Airfoil Testing
Author(jpn)佐藤, 衛; 神田, 宏; 永井, 伸治
Author(eng)Sato, Mamoru; Kanda, Hiroshi; Nagai, Shinji
Author Affiliation(jpn)宇宙航空研究開発機構研究開発本部風洞技術開発センター; 宇宙航空研究開発機構研究開発本部風洞技術開発センター; 宇宙航空研究開発機構研究開発本部風洞技術開発センター
Author Affiliation(eng)Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA); Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA); Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA)
Issue Date2010-06-30
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA research and development memorandum
宇宙航空研究開発機構研究開発資料
VolumeJAXA-RM-10-006
Publication date2010-06-30
Languagejpn
eng
AbstractIt is well known that the two-dimensionality of the flow field is not maintained in the downstream of the shock waves due to the strong side wall boundary layer effects in 2-D airfoil wind tunnel tests. In the JAXA 0.8m x 0.45m High Reynolds Number Wind Tunnel, this side wall effects can be reduced by boundary layer suction through two suction plates located on the both side walls upstream of the airfoil model. The improvement of the two-dimensionality by the sidewall boundary layer suction is well demonstrated for low Mach number and high angle of attack flow, through the pressure distribution measurement, the span-wise pressure distribution measurement at 90% cord, the oil flow visualization, and the pressure distribution measurement of the wakes (four sections between the side walls). Experimental results obtained would be useful for achieving highly accurate measurement in 2-D wind tunnel tests is in transonic flow.
二次元翼型風洞試験では,側壁境界層の影響を強く受ける.これより翼上面衝撃波下流の二次元性が,保てなくなることが知られている.JAXA 0.8 m x 0.45 m 高レイノルズ数遷音速風洞では,模型位置前方の側壁左右2 箇所で境界層吸取りを行い,その影響を減らすことが可能である.本実験では,模型上面の二次元性に対する境界層吸取り効果を調べるため,圧力分布測定,コード長90 % スパン方向の圧力分布,オイルフロー,及び模型後流圧力分布(側壁から4 断面)測定を行った.その結果,低マッハ数,高迎角については二次元性が改善され,精度の高い二次元風洞試験法のための知見を得ることができた.
DescriptionOriginal contains color illustrations
形態: カラー図版あり
KeywordsSidewall Boundary Layer, Airfoil Testing, Transonic
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0064671000
Report NoJAXA-RM-10-006
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/21408


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