An Interactive Boundary-Layer Method for Unsteady Airfoil Flows. 1. Quasi-Steady-State Model

Abstract

An interactive boundary-layer method previously developed and tested for steady flows is used here in a quasi-steady manner to examine the evolution of the flow behavior of airfoils subject to harmonic oscillation and ramp-type motions. The calculations encompass the airfoil and wake flows at angles of attack which lead to separation. The results quantify the effects of the viscous boundary layer and wake on the variation of lift coefficient with angle of attack and reduced frequency. These effects are shown to be large at angles of attack which involve boundary-layer separation. Keywords: Boundary layer flow; Flow separation; Fluid mechanics; Oscillating airfoils; Stalling; Lift coefficients; Unsteady motion.

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Document Details

Document Type
Technical Report
Publication Date
Feb 21, 1990
Accession Number
ADA221220

Entities

People

  • Hong-ming Jang
  • Tuncer Cebeci

Organizations

  • Douglas

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Frequency
  • Hydrodynamics
  • Inviscid Flow
  • Layers
  • Reynolds Number
  • Steady Flow
  • Steady State
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.