The development of a reduced-order unsteady airfoil theory is described for application to subsonic compressible flows with variable free-stream Mach number. The airfoil theory, which is suitable for application to most types of blade element based comprehensive helicopter rotor analyses, is developed for arbitrary, time-dependent combined variations in angle of attack and Mach number. The approach is validated using computational fluid dynamics (CFD) solutions based on the Euler equations. The results show that blade element unsteady aerodynamic theories generally give good results only if the local Mach number variations are small in amplitude and vary slowly in time (i.e., a nearly quasi-steady assumption). However, helicopter rotor problems involve significant non-steady variations in local Mach number at the blade element level and so violate the quasi-steady Mach number assumptions. The new model is developed using linear indicial theory as a basis, and shows excellent agreement with direct CFD solutions for a wide range of flow conditions. For supercritical flows, nonlinearities associated with the formation and movement of shock waves are observed in the CFD solutions, which are responsible for nonlinearities in the lift and pitching moment. The estimation of the pitching moment is found to be particularly challenging because it is sensitive to these nonlinear phenomena. Overall, the new approach provides significant improvements in sectional airloads predictions over existing methods that might be used in various types of comprehensive helicopter rotor analyses.


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    Titel :

    Unsteady aerodynamic modeling with time-varying free-stream mach numbers


    Weitere Titelangaben:

    Simulation der instationären Umströmung eines Hubschrauberrotors bei zeitlich variabler MachZahl der Zuströmung


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2006


    Format / Umfang :

    20 Seiten, 66 Bilder, 1 Tabelle, 40 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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