Static-Thrust Measurements of the Aerodynamic Loading on a Helicopter Rotor Blade
Abstract
An experimental investigation of the aerodynamic loading on a 15-foot-diameter helicopter rotor blade in static thrust was conducted for a tip-speed range of 400 to 500 feet per second and disk loads of zero to about 2.5 pounds per square foot. The chordwise pressure distributions at five spanwise stations are presented and a comparison is made between the measured spanwise loading and a simple theoretical loading modified by an approximate correction for a finite number of blades. The variation of spanwise load distribution near the blade tip with thrust indicates that the blade tip loss is proportional to the thrust coefficient.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1956
- Accession Number
- ADA377309
Entities
People
- John P. Rabbott Jr.
Organizations
- National Aeronautics and Space Administration