Measurements of unsteady pressure distributions and dynamic deformations on an SST elastic arrow-wing model

• Material Type: 文書・図像類
• Title: Measurements of unsteady pressure distributions and dynamic deformations on an SST elastic arrow-wing model
• Author/Editor: 玉山, 雅人; 斉藤, 健一; 松下, 洸; 外立, 政隆; 中道, 二郎; Tamayama, Masato; Saito, Kenichi; Matsushita, Hiroshi; Hashidate, Masataka; Nakamichi, Jiro
• Author Heading: 玉山, 雅人; 斉藤, 健一; 松下, 洸; 外立, 政隆; 中道, 二郎; Tamayama, Masato; Saito, Kenichi; Matsushita, Hiroshi; Hashidate, Masataka; Nakamichi, Jiro
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1999-06
• Publication Date (W3CDTF): 1999-06
• Alternative Title: SST弾性アロー翼モデルにおける非定常圧力分布および動的変位の測定
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory
• No. or year of volume/issue: 1387T
• Volume: 1387T
• Pages: 1-11
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: eng
• Subject Heading: SST; 超音速輸送機; アロー翼; 遷音速流; 非定常空力特性; 非定常圧力分布; 圧力分布測定; 動的変位測定; 弾性翼モデル; 遷音速風洞試験; supersonic transport; arrow wing; transonic flow; unsteady aerodynamic characteristic; unsteady pressure distribution; pressure distribution measurement; dynamic deformation measurement; elastic wing model; transonic wind tunnel test
• Target Audience: 一般
• Note (General): 2段に後退した半載のSST(超音速輸送機)アロー翼を用いて、遷音速領域で非定常圧力分布を計測した。翼は1次の固有振動数が9.79Hzの弾性模型である。46点の非定常圧力変換器を埋め込んだ圧力孔と、他に45点の圧力孔を2列のセミスパン位置に設け、非定常および定常圧力分布を各々計測した。定常及び非定常圧力を別々に計測し、適時にアンプのゼロバランスをとることにより、圧力変換器に生じる温度ドリフトの影響を取り除いた。この結果、アンプゲインの値を高めることが可能になり、S/N(信号対雑音)比の向上につながった。また翼模型の動的変位データを、光ファイバとCCD(電荷結合素子)カメラを用いて計測した。翼後縁に設けたフラップの運動により、翼周りの流れに非定常性を励起した。フラップは平均舵角周りに最高30Hzの周波数で加振した。実験結果により、模型の振動モードは1次の共振振動数に近いフラップ振動数で変化し、この変化が非定常圧力分布にも現れることが確認できた。揚力およびモーメントの非定常成分は、非定常圧力分布を積分して求めた。また、非定常空力係数に関しては、翼の内舷ではフラップの振動が強く影響し、外舷では翼の振動自体が強く影響することがわかった。; Unsteady pressure distributions were measured in a series of experiments in the transonic regime for a double-swept-back semi-span SST (Supersonic Transport) arrow wing model. The wing is an elastic model, the first natural frequency is 9.79 Hz. Forty-six unsteady pressure transducers and 45 pressure orifices were embedded at two semi-span stations to measure unsteady and steady pressure distributions respectively. The influence of temperature drifts in the wind tunnel could be effectively removed from the pressure transducer signal by timely taking of zero-balance. As a result, the gain of amplifiers was able to be raised, and then high S/N (Signal to Noise) ratio achieved. Dynamic deformation data of the wing model were also measured, using optical targets and CCD (Charge Coupled Device) cameras. The flow field around the model was excited by a trailing edge flap which was oscillated around a mean deflection angle in the frequency range up to 30 Hz. The model vibration mode changed at the flap frequency near the model first resonance. The unsteady pressure distributions were affected by this change of vibration mode. Unsteady lift and moment coefficients were derived from unsteady pressure distributions. Of particular role is the fact that while the unsteady aerodynamic coefficients were affected strongly by the flap motion at the inboard wing section, they were influenced by the wing vibration at the outboard wing section.; 資料番号: AA0001978000; レポート番号: NAL TR-1387T
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=40614&item_no=1&attribute_id=31&file_no=1
• Access Restrictions: 限定公開
• 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