Tests of Full-Scale Helicopter Rotors at High Advancing Tip Mach Numbers and Advance Ratios

Abstract

As a continuation of the studies of reference 1, three full-scale helicopter rotors have been tested in the Ames Research Center 40- by 80-foot wind tunnel. All three of them were two-bladed, teetering rotors. One of the rotors incorporated the NCAA 0012 airfoil section over the entire length of the blade. This rotor was tested at advance ratios up to 1.05. Both of the other rotors were tapered in thickness and incorporated leading-edge camber over the outer 20 percent of the blade radius. The larger of these rotors was tested at advancing tip Mach numbers up to 1.02. Data were obtained for a wide range of lift and propulsive force, and are presented without discussion.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 2015
Accession Number
AD1004036

Entities

People

  • James C. Biggers
  • John Iii L. Mccloud
  • Robert H. Stroub

Tags

DTIC Thesaurus Topics

  • Blade Tips
  • Blades
  • California
  • Data Reduction
  • Electronic Mail
  • English Language
  • Helicopter Rotors
  • Helicopters
  • Language Translation
  • Leading Edges
  • Mach Number
  • Space Sciences
  • Symposia
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.