PROBLEM TO BE SOLVED: To suppress a boundary layer from flowing into an intake while suppressing air flow from concentrating at a side part of the intake.SOLUTION: A bump 21 which is smoothly raised from a front of an aircraft and formed with a width W2 broader than an intake 10a is provided at a part positioned just before the intake 10a on a surface of a fuselage 20 of the aircraft.SELECTED DRAWING: Figure 2

    【課題】インテーク側部での気流の集中を抑制しつつインテークへの境界層の流入を抑制する。【解決手段】航空機の胴体20の表面のうち、インテーク10aの直前に位置する部分には、機体前方から滑らかに隆起しつつインテーク10aよりも広い幅W2に形成されたバンプ21が設けられている。【選択図】図2


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    Title :

    INTAKE STRUCTURE OF AIRCRAFT


    Additional title:

    航空機のインテーク構造


    Contributors:
    SATO KAZUNARI (author) / ISO HIDEO (author) / OSUGA TAKESHI (author)

    Publication date :

    2016-10-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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