並列タイトル等Studies of Turbojet Engine Noise Suppression Part 2-Experimental Study of Jet Engine Noise Suppression with a JR100H-1P Turbojet Engine as the Noise Source
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Five acoustically treated inlet-duct configurations and one acoutically treated jet pipe were fabricated, tested and evaluated. Far-field sound pressure levels (at a distance of SOm from the engine) andengine performance data were obtained to evaluate the performance of the test configurations. Sound power attenuation spectra for treated inlet-duct configurations were shown by an insertion loss technique. For frequencies above peak, the observed attenuations were more than predicted. The effects of SjA (the ratio of treated surface area to duct cross sectional area) on sound powei attenuation were also presented for one-third octave band center frequency 4KHz. The increase of a noise floor due to forward radiated jet noise was observed with the increase of the engine speeds. The performance of the treated jet pipe could not be evaluated by one-third octave band analysis adopted here.
資料番号: NALTM0271000
レポート番号: NAL TM-271
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