This paper reports result of an experimental study in the NASA Glenn Icing Research Tunnel (IRT) to evaluate how well the current recommended scaling methods developed for fixed-wing unprotected surface icing applications might apply to representative rotor blades at finite angle of attack. Unlike the fixed-wing case, there is no single scaling method that has been systematically developed and evaluated for rotorcraft icing applications. In the present study, scaling was based on the modified Ruff method with scale velocity determined by maintaining constant Weber number. Models were unswept NACA 0012 wing sections. The reference model had a chord of 91.4 cm and scale model had a chord of 35.6 cm. Reference tests were conducted with velocities of 76 and 100 kt (39 and 52 m/s), droplet MVDs of 150 and 195 fun, and with stagnation-point freezing fractions of 0.3 and 0.5 at angle of attack of 0deg and 5deg. It was shown that good ice shape scaling was achieved for NACA 0012 airfoils with angle of attack lip to 5deg.


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    Titel :

    Evaluation of Scaling Methods for Rotorcraft Icing


    Beteiligte:

    Kongress:

    65th Annual Forum and Technology Display (AHS Forum 65) ; 2009 ; Grapevine, TX, United States


    Erscheinungsdatum :

    2010-03-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Evaluation of Scaling Methods for Rotorcraft Icing

    Tsao, J.C. / Kreeger, R. / AHS International | British Library Conference Proceedings | 2009


    Further Evaluation of Scaling Methods for Rotorcraft Icing

    Tsao, J.-C. / Kreeger, R. / Society of Automotive Engineers | British Library Conference Proceedings | 2011


    Further Evaluation of Scaling Methods for Rotorcraft Icing

    Tsao, Jen-Ching / Kreeger, Richard | SAE Technical Papers | 2011


    Rotorcraft icing

    Emerald Group Publishing | 2008


    Rotorcraft icing - progress and potential

    NATO, Flight Mechanics Panel | TIBKAT | 1986