Accession Number:

ADA089766

Title:

Aerodynamic Characteristics of Three Helicopter Rotor Airfoil Sections at Reynolds Numbers From Model Scale to Full Scale at Mach Numbers From 0.35 to 0.90.

Descriptive Note:

Technical paper,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s):

Report Date:

1980-09-01

Pagination or Media Count:

85.0

Abstract:

An investigation was conducted in the Langley 6- by 28-Inch Transonic Tunnel to determine the two-dimensional aerodynamic characteristics of three helicopter rotor airfoils at Reynolds numbers from typical model scale to full scale at Mach numbers from about 0.35 to 0.90. The model-scale Reynolds numbers ranged from about 0.7 times 10 to the 6th power to 1.5 times 10 to the 6th power and the full-scale Reynolds numbers ranged from about 3.0 times 10 to the 6th power to 6.6 times 10 to the 6th power. The airfoils tested were the NACA 0012 0 deg Tab, the SC 1095-R8, and the SC 1095. Both the SC 1095 and the SC 1095-R8 airfoils a had trailing-edge tabs. The results of this investigation indicate that Reynolds number effects can be significant on the maximum normal-force coefficient and all drag-related parameters namely, drag at zero normal force, maximum normal-force--drag-ratio, and drag-divergence Mach number. In general, the increments in these parameters at a given Mach number owing to the model-scale to full-scale Reynolds number change are different for each of the airfoils. Author

Subject Categories:

  • Aerodynamics
  • Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE