並列タイトル等Transition Analysis on Axisymmetrical Body at nonzero angle of attack in supersonic flow
タイトル（掲載誌）独立行政法人航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-59
一般注記In the development of a supersonic natural laminar flow wing in the NEXST-1 program, a transition analysis code (LSTAB code) based on a current e^N method was originally developed. Recently to improve the precision of the analysis method, a new analysis procedure was investigated. This procedure consists of estimating laminar boundary layer based on CFD analysis and computing stability characteristics by LSTAB code. To verify the procedure, two simple configurations of a sharp cone and the nose cone of the NEXST-1 airplane were analyzed. Although they are axisymmetric bodies, they have very complex flowfield at nonzero angle of attack (AOA). Therefore, it is supposed that present analysis procedure is effective to analyze their transition characteristics. In this article, it is numerically shown that the cross flow instability on the side surface is dominant on transition phenomenon at nonzero AOA.
資料番号: NALSP0059001
レポート番号: NAL SP-59
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43573&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