Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip

Abstract

An investigation was conducted in the Langley Transonic Dynamics Tunnel to obtain data to permit evaluation of paddle-type tip technology for possible use in future U.S. advanced rotor designs. Data were obtained for both a baseline main-rotor blade and a main-rotor blade with a paddle-type tip. The baseline and paddle-type tip blades were compared with regard to rotor performance oscillatory pitch-link loads and 4-per-rev vertical fixed-system loads. Data were obtained in hover and forward flight over a nominal range of advance ratios from 0.15 to 0.425. Results indicate that the paddle-type tip offers no performance improvements in either hover or forward flight. Pitch-link oscillatory loads for the paddle-type tip are higher than for the baseline blade whereas 4-per-rev vertical fixed-system loads are generally lower.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1997
Accession Number
ADA406400

Entities

People

  • Jeffrey D. Singleton
  • Kevin W. Noonan
  • Matthew L. Wilbur
  • William T. Yeager Jr.

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Characteristics
  • Aircrafts
  • Army Aviation
  • Data Acquisition
  • Figure Of Merit
  • Geometry
  • Helicopters
  • Hydraulic Actuators
  • Mach Number
  • Measurement
  • Military Research
  • Strain Gages
  • Test And Evaluation
  • Vehicles
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Climatology