Numerical simulation of flows in curved diffusers with crosssectional transitioning using a threedimensional viscous analysis
Abstract
A three dimensional analysis for fully viscous, subsonic, compressible flow is evaluated. An approximate form of the Navier Stokes equations is solved by an implicit spatial marching technique. Calculations were made for flow in a circular S duct and in the F 16 inlet duct. The computed total pressure contours and secondary flow velocity vectors are presented. Qualitative comparisons with experiment are shown for both ducts. The analysis is used to show how the cross section transitioning in the F 16 inlet suppresses the development of a secondary flow vortex.
 Publication:

Presented at 19th Aerospace Sci. Meeting
 Pub Date:
 January 1981
 Bibcode:
 1981aesc.meet...12T
 Keywords:

 Computational Fluid Dynamics;
 Duct Geometry;
 Numerical Flow Visualization;
 Three Dimensional Flow;
 Transition Points;
 Viscous Flow;
 F16 Aircraft;
 Flow Velocity;
 Inlet Pressure;
 NavierStokes Equation;
 S Curves;
 Secondary Flow;
 Vortices;
 Fluid Mechanics and Heat Transfer