並列タイトル等高亜音速流における二次元ハイブリッド層流制御翼の研究 (その1)基本翼型NLAM78の空力特性
タイトル(掲載誌)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1076
一般注記The present paper describes the experimentally determined aerodynamic characteristics of the NLAM 78 airfoil section, a natural-laminar airfoil designed in Ref.1, over the Mach number range 0.6 to 0.85 and angles of incidence from -1 to 4 as well as the Reynolds number 8, 16 and 32 million, respectively. The airfoil section was selected as the basic airfoil for the hybrid laminar flow control airfoil study which will be described in part 2. The test was executed in the NAL two-dimensional transonic wind tunnel with a test section of 0.3m×1.0m where measurements of the static pressure on the airfoil surfaces and the wake traverse were made. The test has shown that natural laminar airfoil characteristics are maintained for a flow condition of Mach numbers as high as 0.8 and angles of incidence up to 1deg, and that the lift to drag ratio L/D for the condition takes very high values of 72~85 depending on the Reynolds number. Also it shows that for the flow condition the drag divergence Mach number is about 0.82 and drag creep phenomena are rarely observed. Comparison with the flight data given in Ref.1 shows quite satisfactory agreement. Also comparison with some supercritical airfoil with almost the same thickness ratio as the present airfoil confirms the superiority of the aerodynamic characteristics of the NLAM 78 airfoil.
資料番号: NALTR1076000
レポート番号: NAL TR-1076
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45335&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース(IRDB)(機関リポジトリ)
提供元機関・データベース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