並列タイトル等Wind Tunnel Wall Interference Correctionat Subsonic Speeds
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16
一般注記In the wall interference correction of the wind tunnel tests, the fundamental equation of the flow field must be linear everywhere inside the test section. However, the estimated wall interference corrections are often reasonable even in non-linear cases. Some test results obtained at the NAL's two-dimensional wind tunnel show the correction method is available even in the flow of Mach number 0.8. Available mathematical models for the ventilated wall characteristics are not enough accurate for the wall interference estimation. So, it is better to use the pressure distributions on the wind tunnel walls in place of the mathematical model to estimate the ventilated wall interference. This method is available in case of estimating the two-dimensional wall interference. It is difficult to measure reliable pressure distributions over the four wall planes of the test section. So, the method has not been available in case of estimating the three-dimensional wall interference. In principle, test section with the adaptive walls will be solved the wall interference problem even in the transonic flow. More than 20 two-dimensional test sections with the adaptive walls have been in use in the world.
資料番号: NALSP0016047
レポート番号: NAL SP-16
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