Accession Number : ADA117397

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

Descriptive Note : Conference paper,

Corporate Author : ARMY RESEARCH AND TECHNOLOGY LABS HAMPTON VA STRUCTURES LAB

Personal Author(s) : Bingham,Gene J

PDF Url : ADA117397

Report Date : 18 Jun 1982

Pagination or Media Count : 14

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.

Descriptors :   *Rotor blades(Rotary wings), *Twist(Motion), Operational effectiveness, Flight, Hovering, Helicopters, Airfoils, Taper, Advanced weapons, Helicopter rotors, Roll, Pitch(Inclination), Lift, Coefficients, Planform, Thrust, Wind tunnel tests

Subject Categories : Aerodynamics
      Helicopters
      Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE