To provide a transonic speed profile capable of further reducing pressure drag, a wing comprising such a profile and an aircraft comprising such a wing.SOLUTION: A profile 11 is formed into a shape in which, a pressure coefficient of a static pressure in a wing chord direction of a front edge 12 of the profile is, in z/c=0.015, equal to or less than -0.04 (z is a coordinate of a direction vertical to an air flow direction in a plane forming the profile with the front edge as a reference (positive direction is a wing top surface direction, negative direction is a wing lower surface direction) and c is a chord length). Therefore, since the start of the pressure distribution is steep, the pressure drag can be reduced.SELECTED DRAWING: Figure 2

    【課題】圧力抵抗をこれまで以上に低減することができる遷音速翼型、そのような翼型を有する翼及びそのような翼を有する航空機を提供すること。【解決手段】翼型11は、その前縁12の翼弦方向の静圧の圧力係数Cpがz/c=0.015で−0.04以下となる形状を有する。(z:前縁を基準とし、翼型を形成する面内で気流方向に垂直な方向の座標(正は翼上面方向、負は翼下面方向)、c:翼弦長)。これにより、圧力分布の立ち上がりが急峻になることで、圧力抵抗を小さくすることができるようになる。【選択図】図2


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    Title :

    TRANSONIC SPEED PROFILE, WING AND AIRCRAFT


    Additional title:

    遷音速翼型、翼及び航空機


    Contributors:

    Publication date :

    2019-06-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten



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