Hamilton Standard, Pratt a. Whitney and NASA Lewis jointly conducted an icing test program during the 1986-87 and 1987-88 icing seasons at the Fluidyne Icing Tunnel. The testing consisted of evaluating the icing characteristics and aerodynamic performance characteristics of two thin, 2-D airfoil sections. The two airfoils were a NACA Series 16-203 and a Hamilton Standard PF1-304, 3 and 4 % thickness-to-chord ratio airfoils, respecticely. These airfoils are representative of the thin airfoils currently being evaluated for Prop-Fan propulsion systems. The tests were conducted over a wide range of icing conditions, angles-of-attack, and Mach numbers (0.3 to 0.8). At each test point, a record of the accreted ice shape and weight was taken. Airfoil drag was measured via a drag wake rake. Airfoil surface pressures were also recorded during each run. Data trends are presented and comparisons made with published iced airfoil aerodynamic performance correlations.
Prop-fan airfoil icing characteristics
Vereisungsverhalten von Tragfluegeln an Trubopropflugzeugen
AIAA-Papers ; Jan ; 1-32
1988
32 Seiten, 16 Bilder, 2 Tabellen, 14 Quellen
Conference paper
English
Prop-fan airfoil icing characteristics
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