Accession Number:

AD0743232

Title:

Experimental Investigation of Effects of Blade Section Camber and Planform Taper on Rotor Hover Performance

Descriptive Note:

Final rept. Oct 1970-Oct 1971

Corporate Author:

UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT

Personal Author(s):

• Bellinger, E. Dean

Report Date:

1972-03-01

Pagination or Media Count:

84.0

Abstract:

An experimental and analytical investigation was conducted to determine the effects of blade section camber and blade planform taper on helicopter rotor hover performance and to assess the accuracy of several theoretical methods in predicting such performance. The tests were conducted using small scale model rotors nominally 4 feet in diameter operating in and out of ground effect at full-scale tip speeds. The NACA 23112 airfoil, which is a section specifically designed to produce very low pitching moments such as required for helicopter blade applications, was selected for the cambered blade. A nominal taper ratio of 21 was selected for the tapered blade tests.

Descriptors:

• *HELICOPTER ROTORS
• *HOVERING
• *ROTOR BLADES(ROTARY WINGS)
• AIRCRAFT MODELS
• CAMBER
• FLUID DYNAMICS
• MODEL TESTS
• TAPER
• VORTICES
• WAKE

Subject Categories:

• Helicopters
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE