The effect of a simulated glaze-ice accretion on the aerodynamic performance of a NACA 0012 airfoil was studied experimentally. Two ice shapes were tested: one from an experimentally measured accretion, and one from an accretion predicted using a computer model given the same icing conditions. Lift, drag, and pitching moment were measured for the airfoil with both smooth and rough ice shapes. The ice shapes caused large lift and drag penalties, primarily due to large separation bubbles. Surface pressure distributions clearly showed the regions of separated flow. The aerodynamic performance of the two shapes compared well at positive, but not negative, angles of attack.
Experimental aerodynamic characteristics of an NACA 0012 airfoil with simulated glaze ice
Journal of Aircraft ; 25
1988-09-01
Miscellaneous
No indication
English
Experimental aerodynamic characteristics of NACA 0012 airfoils with simulated glaze and rime ice
Online Contents | 2001
|Experimental aerodynamic characteristics of NACA 0012 airfoils with simulated glaze and rime ice
SAGE Publications | 2001
|