PROPELLERS WITH DISTORTED INFLOW

Abstract

An investigation was made of the steady-state reaction of a propeller to velocity perturbations induced by deflected control surfaces located upstream of the propeller. Theoretically, actuator disk theory is used, first, to represent the control surfaces and introduces a distortion into the flow and, secondly, to represent the action of the propeller when exposed to the distorted flow. The problem is reduced to a boundary value problem by linearizing the equations of motion and the continuity equation and then solved by proper choice of boundary and matching conditions at the actuator disks. The experimental results show that the maximum reactive force of the propeller is abut 34% of the control surface force. This maximum occurs for a 10-bladed propeller with lesser percentages occurring for propellers of 2 and 5 blades. Practically no variation with advance ratio and spacing distance was measured. The theoretical method can easily be extended to the case of a ducted rotating device.

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Document Details

Document Type
Technical Report
Publication Date
Jun 12, 1963
Accession Number
AD0408556

Entities

People

  • J. J. Eisenhuth

Organizations

  • Pennsylvania State University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Asymptotic Series
  • Bessel Functions
  • Computational Science
  • Computer Programs
  • Computers
  • Control Surfaces
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Instrumentation
  • Measurement
  • Propeller Blades
  • Shape
  • Steady State
  • Three Dimensional
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Control Systems Engineering.
  • Mathematics or Statistics

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers