Investigation of the Effect of a Tip Modification and Thermal De-Icing Air Flow on Propeller Performance

摘要

Tests of 12.208 ft diameter, two-blade, hollow steel propeller before and after alteration for thermal anti-icing have been made to determine effect of alterations on propeller efficiency. Propeller was tested on 200 hp dynamometer at blade angles ranging from 25 to 80 deg at 425 mph. Overall loss of propeller efficiency caused by tip alteration with internal flow was 3% at lower values and 0.5% at 2.8 advanced ratio. Coefficient of mass flow of de- icing air increased with advance ratio and decreased with increase in rotational speed for thermal de-icing propeller.