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Other TitleWind tunnel wall interferences for a half-span aircraft model testing with high-lift devices
Author(jpn)村山, 光宏; 横川, 譲; 田中, 健太郎; 山本, 一臣; 伊藤, 健
Author(eng)Murayama, Mitsuhiro; Yokokawa, Yuzuru; Tanaka, Kentaro; Yamamoto, Kazuomi; Ito, Takeshi
Author Affiliation(jpn)宇宙航空研究開発機構航空プログラムグループ; 宇宙航空研究開発機構航空プログラムグループ; 菱友システムズ; 宇宙航空研究開発機構航空プログラムグループ; 宇宙航空研究開発機構研究開発本部
Author Affiliation(eng)Aviation Program Group, Japan Aerospace Exploration Agency (APG)(JAXA); Aviation Program Group, Japan Aerospace Exploration Agency (APG)(JAXA); Ryoyu Systems; Aviation Program Group, Japan Aerospace Exploration Agency (APG)(JAXA); Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Issue Date2009-02-27
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication titleJAXA special publication: Proceedings fo 40th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2008
宇宙航空研究開発機構特別資料: 第40回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2008論文集
Publication date2009-02-27
AbstractIn this paper, wind tunnel wall interferences due to high-lift half-span model testing are investigated in detail to understand the differences between the flows in the wind tunnel and free-air conditions. Three-dimensional flow computations over a half-span wind tunnel testing model of a realistic high-lift aircraft wing-body configuration with a nacelle-pylon tested at JAXA are performed using an unstructured mesh method. Influence of a spacer to avoid interferences between the model and the boundary layer of the bottom wind tunnel wall when the half-span model is mounted vertically on the wind tunnel is investigated in the computations with/without the spacer. Influence of the height of the spacer is estimated by the computations with three heights of the spacer in the free-air conditions with/without the floor boundary layer. The results showed that the spacer and floor boundary layer generated large positive and negative velocity changes in the plane to assume the symmetric condition and changed the effective angle of attack locally near the fuselage. The changes reduced drag especially at high angle of attack and generated the difference of C(sub L)-C(sub D) curve. Through the investigations, a height of the boundary layer spacer related to the displacement thickness of the floor boundary layer showed less difference with the results in the free-air conditions.
Description形態: カラー図版あり
会議: 第40回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2008. 会期: 2008年6月12日-6月13日. 会場: 東北大学片平キャンパス
Document TypeTechnical Report
JAXA Category特別資料
Report NoJAXA-SP-08-009

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