Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller Page: 2 of 55
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA RM No . L8E26
NATIONAL ADVISORY COMM1TTE FOP AERONAUTICS
RESEARCH MEMORANDUM N '
AERODYNAMIC CHARACTERISTICS AT HIGH SPEEDS OF A '
TWO-BLADE NACA 10-(3)(062)-045 PROPELLER AflD OF
A TWO-BLADE NACA 10-(3) (08) -045 PROPELLER
By William Solomon
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
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 200 to 550
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.
The aerodynamic characteristics of a series of 10-foot-diameter
propellers are-being investigated in the Langley 16-foot high-speed tunnel
in a comprehensive propeller research program. Using high-critical-speed
NACA 16-series airfoil sections (reference i), these propellers are designed
to have Betz minimum induced-energy-loss loading (reference 2) for a blade
angle of 450 at the 0.7 radius, when used as a four-blade propeller oper-
ating at an advance ratio of approximately 2.1. The ultimate purpose of
the program is to determine the influence upon propeller performance of
propeller design factors and of compressibility; the propeller tests
reported herein form part of the investigation of the effects of blade--
section thickness ratio. However, comprphensive analysis has been post-
poned in favor of early presentation of the available data on the
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Solomon, William. Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller, report, October 1, 1948; (https://digital.library.unt.edu/ark:/67531/metadc57659/m1/2/: accessed June 19, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.