Periodic flows at transonic Mach numbers have been a serious aerodynamic problem since the early days of flight at transonic speeds. The buffering which occurs can cause serious discomfort to pilot and passengers and in severe cases may result in structural deformation or even failure. Civil transport aircraft are nowadays flying much closer to the speed of sound and military aircraft also spend a large proportion of their flying time in this potentially hazardous Mach number region. Periodic flows can also occur in wind tunnels if attention is not paid to the design of such features as model support struts and instrumentation fairings. Consequently, it is very important to understand fully the cause of periodic flows at transonic speeds in order to be able to prevent their occurrence in new designs and to be able to apply cures to any problems in existing designs. This paper will present experimental results which describe some of the problems which arise in trying to simulate such flows with large scale unsteadiness. An explanation of the physics of the cause of periodic flows at transonic speeds will be given, along with results of several techniques which have successfully eliminated the problem on the 14 % thick Biconvex aerofoil and the NACA 0012 aerofoil.


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    Title :

    The simulation and suppression of 2-D periodic flows at transonic speeds


    Additional title:

    Simulation und Unterdrückung zweidimensionaler Strömung bei transsonischen Geschwindigkeiten


    Contributors:
    Gibb, J. (author)


    Publication date :

    1989


    Size :

    27 Seiten, 13 Bilder, 1 Tabelle, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English