The Aerodynamic Influences of Rotor Blade Taper, Twist, Airfoils and Solidity on Hover and Forward Flight Performance.

Abstract

The study began with the design of an advanced rotor for the UH-1 helicopter. The initial design goal was to reduce hover power required by 8% without degrading forward flight performance. This reduction was to be accomplished with an aircraft gross weight of 8050 pounds while operating at an altitude of 4000 feet and a temperature of 95 deg F. The study indicated that the design goal could be exceeded. Based on this result, models of the baseline and advanced blade have been evaluated in the Langley V/STOL wind tunnel and the analytical study has been extended to other helicopter configurations within the US Army inventory. This paper is to describe the design philosophy applied. The influence of blade planform and twist on rotor performance are considered first for hover and then for forward flight. These influences initially are made independent of airfoil characteristics; after the influences of blade geometry are described, the airfoil requirements are addressed.

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Document Details

Document Type
Technical Report
Publication Date
Jun 18, 1982
Accession Number
ADA117397

Entities

People

  • Gene J. Bingham

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Blade Tips
  • Blades
  • Coefficients
  • Computer Programs
  • Dynamic Pressure
  • Figure Of Merit
  • Flight
  • Helicopter Rotors
  • Inboard
  • Mach Number
  • Planform
  • Standards
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Systems Analysis and Design