Computational Research on Inviscid, Unsteady, Transonic Flow Over Airfoils.

Abstract

The inviscid transonic flow over an NACA 64A410 airfoil oscillating in pitch in a Mach 0.72 stream was calculated with a program based on the unsteady Euler equations. The airfoil oscillates about a mid-chord axis with attitude alpha = 1 deg + or - 1 deg at reduced frequency k = omega C/U(infinty) = 0.2. The effects of two approximations made in the analysis, handling of boundary conditions at the airfoil surface and at the perimeter of the computation field, have been studied. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1977
Accession Number
ADA037469

Entities

People

  • R. J. Magnus

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Amplitude
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programming
  • Computer Programs
  • Differential Equations
  • Equations
  • Euler Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Frequency
  • Pressure Distribution
  • Steady Flow
  • Transonic Flow
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.