A Navier-Stokes Calculation of the Airfoil Dynamic Stall Process,

Abstract

A time-dependent Navier-Stokes calculation procedure has been applied to the problem of an NACA 0012 airfoil oscillating in pitch in a low Mach number, high Reynolds number environment. The calculated results show many of the known physical features, including sudden suction surface separation, vortices shed at the leading and trailing edges and the return to attached flow at low incidences. Both the lift and moment coefficient curves show the expected features and the calculated wall pressure coefficients show strong correspondence to measured data. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1984
Accession Number
ADP004163

Entities

People

  • S. J.. Shamroth

Tags

DTIC Thesaurus Topics

  • Air Force
  • Coefficients
  • Environment
  • Mach Number
  • Reynolds Number
  • Trailing Edges
  • United States
  • United States Air Force Academy
  • Workshops

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.