Computation of twodimensional turbulent flow at subsonic Mach numbers over thick trailing edges
Abstract
An implicit time marching finite difference method is used to predict two dimensional turbulent flow at a Reynolds number of 440,000 and a Mach number of 0.574 over a shortened NACA 0012 airfoil with a trailing edge of 4.5% thickness and semicircular shape. The flow is found to be unsteady but periodic in the trailing edge region. Thus, lift and drag fluctuate at small amplitudes around mean values and at distinct frequencies.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 August 1982
 Bibcode:
 1982STIN...8233663D
 Keywords:

 Computational Fluid Dynamics;
 Thickness Ratio;
 Trailing Edges;
 Turbulent Flow;
 Two Dimensional Flow;
 Airfoils;
 Finite Difference Theory;
 Mach Number;
 Reynolds Number;
 Fluid Mechanics and Heat Transfer