Aerodynamic Characteristics Obtained from α Sweep Test of the Quiet STOL Experimental Aircraft ASKA
| Autor: | STOLプロジェクト推進本部飛行試験室, Flight Test Team STOL Research Aircraft Project Group |
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| Jazyk: | japonština |
| Rok vydání: | 1991 |
| Předmět: | |
| Zdroj: | 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1112. 1112:11 |
| ISSN: | 0389-4010 |
| Popis: | 「飛鳥」のαスイープ試験データを解析して縦3分力空力係数を求め,縦の空力特性を論ずるとともに,飛行試験結果と風洞試験結果の比較を行った。更に,USBおよび外側フラップ角変化の揚抗特性に及ぼす影響,外側及び内側エンジン故障時の空力特性についても論ずる。ピッチ・アップ及びパス・ダイバージェンスに関して述べるとともに,パワード・リフト機としての揚力構成とパワード・リフト・ファクタについて,飛行試験から直接求めた結果を報告する。 Longitudinal aerodynamic characteristics are one of the most important considerations in aircraft design. Using the National Aerospace Laboratory (NAL) Short Take-Off and Landing (STOL) experimental aircraft, ″ASKA″, an alpha sweep method was adopted instead of using the conventional discrete method to investigate ASKA′s longitudinal aerodynamic characteristics. ASKA′s longitudinal aerodynamic characteristics are discribed based on analysis of the test results. In addition, longitudinal aerodynamic coefficients obtained from flight tests are compared with the ASKA′s wind tunnel design configuration. ASKA showed a pitch up phenomena during shallow Upper Surface Blowing(USB) flap angles, and also encountered path divergence in the flap-up configuration, being a significant phenomena for a powered-lift aircraft. Powered-lift aircraft′s lift coefficient consists of basic lift due to wing and flaps, direct jet thrust, and supercirculation. This lift build-up is described using calculation results of flight test data. The powered-lift factor, a key parameter for powered-lift aircraft, is also described. 資料番号: NALTR1112000 レポート番号: NAL TR-1112 |
| Databáze: | OpenAIRE |
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