A theoretical model has been established which is applicable to both propeller and helicopter systems that determines the effect of rime ice accretion on the thrust coefficient, power coefficient, and efficiency as a function of time in a natural icing condition. Theoretical comparisons have been made with experimentally determined decrease in propeller thrust coefficient and efficiency for five natural icing conditions with good agreement. The present analytical model is also applicable to the helicopter case, where the method predicts radial and azimuthal rotor blade ice shapes in addition to torque rise as a function of time in a natural icing condition.
Performance degradation of propeller/rotor systems due to rime ice accretion
Aerospace Sciences Meeting ; 1982 ; Orlando, FL
1982-01-01
Conference paper
No indication
English
Predicting rime ice accretion on airfoils
AIAA | 1985
|Rime Ice Accretion and Its Effect on Airfoil Performance
NTIS | 1982
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