Accession Number : ADA134633

Title :   Parametric Tip Effects for Conformable Rotor Applications.

Descriptive Note : Technical memo.,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s) : Mantay,W R ; Yeager,W T , Jr

PDF Url : ADA134633

Report Date : Aug 1983

Pagination or Media Count : 31

Abstract : A research study was initiated to systematically determine the impact of selected blade tip geometric parameters on aeroelastically conformable rotor performance and loads characteristics. The model articulated rotors included baseline and torsionally soft blades with interchangeable tips. Sven blade tip designs were evaluated on the baseline rotor and three tip designs were tested on the torsionally soft blades. The designs incorporated a systematic variation in three geometric parameters: sweep, taper, and anhedral. The rotors were evaluated in the NASA Langley Transonic Dynamics Tunnel at several advance ratios, lift and propulsive force values, and tip Mach numbers. Based on the test results, tip parameter variations generated significant rotor performance and loads differences for both baseline and torsionally soft blades. Azimuthal variation of elastic twist generated by the tip parameters strongly correlated with rotor performance and loads, but the magnitude of advancing blade elastic twist did not correlate. (Author)

Descriptors :   *Rotor blades(Rotary wings), *Aeroelasticity, Helicopter rotors, Aerodynamic configurations, Adaptive systems, Loads(Forces), Twist(Motion), Torsion, Stiffness, Shape, Taper, Anhedral angle, Elastic properties, Wind tunnel tests

Subject Categories : Helicopters
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE