INVESTIGATION OF AN ISOLATED MONOCYCLIC V/STOL PROPELLER PERFORMANCE AND OSCILLATORY STRESS

Abstract

Test results confirmed: (1) that there is an apparent phase shift of the monocyclic axis at high collective angle, caused by hysteresis in the airfoil's stall characteristics, and (2) that there is an increase in side force as collective angle is increased, caused by a nonlinear variation in airfoil drag with cyclic pitch. The monocyclic propeller test program also included investigation of the effects of control system stiffness on the dynamic response of the propeller and control system. The results indicate that the use of cyclic-blade-pitch control reduces the harmonic content of control system oscillatory loads to basically a first-harmonic response. Higher harmonic loads are present, but their amplitudes are less than 10 percent of the resultant peak-to-peak load, and are therefore considered negligible. The results of the program also indicate that the increase of control system stiffness resulted in an increase in blade-pitch-link oscillatory loads.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1966
Accession Number
AD0629647

Entities

People

  • R. W. De Decker

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Army Aviation
  • Classification
  • Contracts
  • Control Systems
  • Dynamic Response
  • Figure Of Merit
  • Frequency
  • Geometry
  • Harmonic Analysis
  • Phase Shift
  • Propellers
  • Stiffness
  • Test Facilities
  • Tilt Wing Aircraft
  • Tilt Wings

Readers

  • Aerospace Engineering
  • Control Systems Engineering.