航技研120mm×360mmルートビーク管の特性とそれを用いた遷音速二次元翼試験

• Material Type: 文書・図像類
• Title: 航技研120mm×360mmルートビーク管の特性とそれを用いた遷音速二次元翼試験
• Author/Editor: 高島, 一明; 高橋, 宏; 桑野, 尚明; 青木, 竹夫; 星野, 秀雄; 野口, 正芳; 唐沢, 敏夫; 野中, 修; TAKASHIMA, Kazuaki; TAKAHASHI, Hiroshi; KUWANO, Naoaki; AOKI, Takeo; HOSHINO, Hideo; NOGUCHI, Masayoshi; KARASAWA, Toshio; NONAKA, Osamu
• Author Heading: 高島, 一明; 高橋, 宏; 桑野, 尚明; 青木, 竹夫; 星野, 秀雄; 野口, 正芳; 唐沢, 敏夫; 野中, 修; TAKASHIMA, Kazuaki; TAKAHASHI, Hiroshi; KUWANO, Naoaki; AOKI, Takeo; HOSHINO, Hideo; NOGUCHI, Masayoshi; KARASAWA, Toshio; NONAKA, Osamu
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1979-06
• Publication Date (W3CDTF): 1979-06
• Alternative Title: Experimental Studies of the Characteristics of the 120mm×360mm Ludwieg Tube and Measurements of the Pressure Distribution of Transonic Wing Airfoils
• 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: 383
• Volume: 383
• Pages: 21-
• ISSN (Periodical Title): ISSN : 0452-2982
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): The Ludwieg tube is a test facility which has the potential of realizing a higher Reynolds number.In order to obtain the characteristics of the flow in the Ludwieg tube and the performance of wing airfoils at a high Reynolds number at transonic regime,the transonic Ludwieg tube was constructed.The main dimensions are a two-dimensional transonic test section of 120mm×360mm,Mach number range of 0.45 to 1.1,maximum internal pressure of 1080 kPa and a duration time of about 0.1 second.At first,flow characteristics such as the steadiness of the stagnation pressure and Mach number,the duration time of a steady state and so on were obtained experimentally.The timewise change of the stagnation pressure was in the order of 4 per cent.At the region of M＞0.85,steadiness of the Mach number was gradually spoiled as the Mach number increased.Secondly,pressure distribution of the upper surfaces of the two airfoil models were mainly measured.Wing profiles of those models were derived from the exact solutions of the trnic potential flow equation of the hodograph method at NAL.Experimental conditions of the wing airfoil models were;model chord length of 14cm,Mach number range of 0.63 to 0.80,and Reynolds number of 7 to 14 million.The test results showed inclusively good agreement with the results obtained at other wind tunnel tests.These results came from the tests of the lower Reynolds number (4.8～5.2 million) at 2m×2m transonic wind tunnel.For the tests at the Ludwieg tube,the shock wave movement on the upper surface was frequently observed in the short duration run time of 0.05 second.Finally,the constrictions and problems of the Ludwieg tube tests and the approach to the solutions were discussed.; 資料番号: NALTM0383000; レポート番号: NAL TM-383
• Access Restrictions: 限定公開
• Periodical Title (NCID): AN00314334; https://ci.nii.ac.jp/ncid/AN00314334
• 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