Aeordynamic Characteristics of a Two-Blade NACA 10-(3)(062)-045 Propeller and of a Two-Blade NACA 10-(3)(08)-045 Propeller
Abstract
As part of the investigation to determine the influence of blade-section thickness ratio on propeller performance, tests were made in the Langley 16-foot high-speed tunnel to determine the aerodynamic characteristics of the two-blade NACA 10-(3)(062)-045 propeller and of the two-blade NACA 10-(3)(08)-045 propeller. Data were obtained over a blade-angle range from 20 deg to 55 deg as measured at the 0.75-radius station, the various constant values of rotational speed used giving a range of advance ratio from 0.5 to 3.8. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1953
- Accession Number
- ADA377256
Entities
People
- William Solomon
Organizations
- National Aeronautics and Space Administration