低騒音STOL実験機「飛鳥」のαスイープ試験より得られた空力特性

Material type: 文書・図像類

Author: STOLプロジェクト推進本部飛行試験室ほか

Publisher: 航空宇宙技術研究所

Publication date: 1991-05

Material Format: Digital

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Note (General)：: 「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...

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Material Type: 文書・図像類
Title: 低騒音STOL実験機「飛鳥」のαスイープ試験より得られた空力特性
Author/Editor: STOLプロジェクト推進本部飛行試験室
Flight Test Team STOL Research Aircraft Project Group
Author Heading: STOLプロジェクト推進本部飛行試験室
Flight Test Team STOL Research Aircraft Project Group
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1991-05
Publication Date (W3CDTF): 1991-05
Alternative Title: Aerodynamic Characteristics Obtained from α Sweep Test of the Quiet STOL Experimental Aircraft ASKA
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1112
No. or year of volume/issue: 1112
Volume: 1112
Pages: 11-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Subject Heading: Flight Test; Powered-Lift; Upper Surface Blowing; STOL; Super Circulation; Pitch Up
Target Audience: 一般
Note (General): 「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
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