並列タイトル等Test of an Air Inlet Model for Turbofan Engine
タイトル（掲載誌）航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
一般注記Some results of low-speed performance tests with a smaIl-scale model for turbo- fan engine are presented and discussed. The results are as follows: 1) At zero flight speed, the total pressure recovery with a given opening area of the auxiliary inlet ports decreased as the mean axial flow velocity V2 at the fan face increased. 2) In the test range of flight speed Vo, the total pressure recovery with a given opening area of the auxiliary inlet ports increased up to 99% and more as the value of Vo/V2 increased. 3) At any tested combination of Vo with V2, the total pressure recovery increased as the number of the closed auxiliary inlet ports decreased. 4) The observed upstream flow behavior, inlet distortion, and surface static pressure distribution as the function of the value of Vo/V2 are presented and discussed taking the effects of ground clearance and attack angle also into consideration.
資料番号: NALTM0185000
レポート番号: NAL TM-185
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43769&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