This paper summarizes some of the results obtained in a study of two .25 scale propellers tested in the Quiet Flow Facility at the NASA Langley Research Center. Both performance and noise measurements were made over advance ratios from .4 to 1.3, for thrust loadings up to 22 lbs/ft2 and tip Mach numbers up to .82. These data were obtained for validation of noise and performance prediction theories. Scale effects on performance were also examined using data obtained from other tests at .566 and full scale for the two propellers. Finally, the effect on performance and noise of a wake entering the disk plane was examined.