SHROUDED PROPELLER INVESTIGATIONS: PROPELLER TIP CLEARANCE EFFECTS

Abstract

Wind tunnel tests were conducted on a shrouded propeller model in which the propeller diameter was varied for the purpose of measuring the effects of tip to shroud clearance. The basic model tested contained a four-bladed variable pitch propeller operating within a 0.50 chord/diameter ratio shroud. To assist in studying the effect of annulus area on tip clearance, two models having 0.30 and 0.40 hub/tip diameter ratio centerbodies were tested over roughly the same range of propeller tip clearances. Performance of the models was measured throughout a range of advance ratios from zero to roughly 2.20 at several propeller blade pitch settings at zero angle of attack only. Results are presented in the form of force and power coefficients and efficiency varying with propeller tip clearance and rotational speed for forward and static flight conditions.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1961
Accession Number
AD0256533

Entities

People

  • Hans Hoffman
  • Vernon O. Hoehne

Organizations

  • Wichita State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Blade Tips
  • Blades
  • Boundaries
  • Boundary Layer
  • Diameters
  • Dynamic Pressure
  • Engineering
  • Flow
  • Fluid Flow
  • Propeller Blades
  • Propellers
  • Shrouded Propellers
  • Static Pressure
  • Variable Pitch Propellers
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.