This paper examined the wing rock motion of an aircraft model with a configuration of slender fuselage, 81°-swept strake wing, 48°-swept wing and twin vertical tails. These experiments covered the alpha range of 0° to 70° and zero sideslip with a Reynolds number (Re) of 1.2×105.The roll motion pattern can be divided into three regions: No wing rock region (α = 0-20°), micro-vibration region (α = 20°-35° and α = 60°-70°), wing rock region (α = 35°-60°). At the wing rock region, the motion was not induced by asymmetric vortices on slender forebodythrough the analysis of response relationship between wing rock motion and location of nose perturbation.


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    Title :

    Wing Rock Motion of an Aircraft Model at Fixed Angle of Attack


    Contributors:
    Wang, Y.K. (author) / Li, Q. (author) / Shi, W. (author) / Sun, G.L. (author)


    Publication date :

    2013


    Size :

    10 Seiten, 8 Quellen




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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