PROBLEM TO BE SOLVED: To facilitate the use of CAD software to design a tip edge configuration of an aerofoil, and provide benefits to a stall boundary and compressibility boundaries which limit the load carrying capacity and speed of helicopters.SOLUTION: An aerofoil has a main portion of an aerofoil cross section, an inner spanwise root end where the aerofoil in use is secured to a supporting structure, and at an outermost spanwise end outboard of the main portion, beyond a tip station and a tip region, which includes a tip edge. A planform configuration of the tip edge lies on a first Bezier curve constructed from at least four control points, P1, P2, P3 and P4.SELECTED DRAWING: Figure 3
【課題】翼の先端エッジ構成を設計するためのCADソフトウェアの使用を容易にし、ヘリコプターの荷重搬送能力と速度を制限する失速限界と圧縮可能性限界に恩恵を提供する。【解決手段】翼型断面の主要部と、翼が使用中には支持構造にしっかり取り付けられる内側翼幅方向付け根端と、先端ステーション、先端領域を越えた、主要部の翼端寄りの最外側翼幅方向端とを有し、先端領域は先端エッジを含み、先端エッジのプラットフォーム構成は少なくとも4つの制御ポイントP1、P2、P3およびP4から構築された第一のベジエ曲線上に横たわる翼とする。【選択図】図3
AEROFOIL
翼
2017-02-02
Patent
Electronic Resource
Japanese