The Laminar Boundary Layer on a Rotating Blade of Symmetrical Airfoil Shape

Abstract

A theoretical study has been conducted to determine the effects of rotation, inflow, and forward flight on the development of the laminar boundary layer on a helicopter blade. Particular emphasis was placed on the determination of the separation line. In order to faciliate the computation of the inviscid flow about the blade, an 11.9%-thick symmetrical Joukowski airfoil was used. The essential feature of the analysis was the scaling of the chordwise coordinate so that the separation line is invariant with span and time in the transformed coordinate system. The transformed boundary layer equations were expanded in an asymptotic series in span, and the resulting equations were solved. The major effect of rotation is noted as a delay in separation.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1970
Accession Number
AD0880949

Entities

People

  • James C. Williams Iii
  • Warren H. Young Jr.

Organizations

  • North Carolina State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Aspect Ratio
  • Asymptotic Series
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Science
  • Computer Programs
  • Fluid Flow
  • Helicopter Rotors
  • Inviscid Flow
  • Laminar Boundary Layer
  • Lepidoptera
  • Numerical Analysis
  • Pressure Gradients
  • Shear Stresses
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.