超小型飛行機のレイノルズ数領域における４％キャンバー翼型およびＮＡＣＡ００１２翼型の空力特性

DOI Web Site Web Site 被引用文献3件 参考文献29件
  • 手塚 亜聖
    早稲田大学理工学術院基幹理工学部機械科学・航空学科
  • 砂田 保人
    東京大学大学院工学系研究科航空宇宙工学専攻
  • 李家 賢一
    東京大学大学院工学系研究科航空宇宙工学専攻

書誌事項

タイトル別名
  • Aerodynamic Characteristics of 4% Cambered-Plate and NACA0012 Airfoil at the Reynolds Numbers Region for Micro Air Vehicles
  • チョウコガタ ヒコウキ ノ レイノルズスウ リョウイキ ニ オケル 4% キャンバーヨクガタ オヨビ NACA0012ヨクガタ ノ クウリキ トクセイ

この論文をさがす

説明

In the Reynolds number region lower than approximately 1.0 × 105, which corresponds to the Reynolds number region of a Micro Air Vehicle, thinner and sharper leading edge airfoil performs better than thicker and blunter one. This research focuses on the difference in flowfields which are clarified by means of streamline calculation and surface pressure distribution measurement. Numerical studies were performed to the blunt type NACA0012 airfoil and both numerical and experimental studies were performed to the thinner type 4% cambered-plate airfoil. The performance of the NACA0012 airfoil is deteriorated with decreasing Reynolds number, whereas that of the 4% circular arc cambered-plate airfoil is not affected. The deterioration of the NACA0012 airfoil performance is mainly due to the laminar boundary layer separation near the trailing edge; such phenomena are not essential to the performance in the cambered-plate airfoil results. This paper also demonstrates that the flow separation at the trailing edge can be estimated from the temporal amplification factor of the oscillatory mode which is calculated by the global linear stability analysis.

収録刊行物

被引用文献 (3)*注記

もっと見る

参考文献 (29)*注記

もっと見る

関連プロジェクト

もっと見る

キーワード

詳細情報 詳細情報について

問題の指摘

ページトップへ