Effect of a Trailing-Edge Extension on the Characteristics of a Propeller Section

Abstract

Method is presented to evaluate changes in airfoil characteristics resulting from extension of chord at trailing edge of propeller blade section. Method determines changes in angle of zero lift, angle of attack, and difference in these angles (upon which design lift coefficient depends) as function of angle and length of trailing edge extension. Treatment is based on thin-airfoil theory and is concerned only with mean camber line of section. Examples and detailed computations illustrate application of method, which is applicable to all propeller sections. Characteristics obtained were in perfect agreement with data calculated by exact method of arbitrary airfoil theory.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1944
Accession Number
ADA800863

Entities

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Agreements
  • Blades
  • Coefficients
  • Computations
  • Equations
  • Mathematics
  • Potential Theory
  • Pressure Distribution
  • Propeller Blades
  • Propellers
  • Square Roots
  • Stagnation Point
  • Thickness
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Graph Algorithms and Convex Optimization.