Computation of transonic separated wing flows using an Euler/NavierStokes zonal approach
Abstract
A computer program called Transonic Navier Stokes (TNS) has been developed which solves the Euler/NavierStokes equations around wings using a zonal grid approach. In the present zonal scheme, the physical domain of interest is divided into several subdomains called zones and the governing equations are solved interactively. The advantages of the Zonal Grid approach are as follows: (1) the grid for any subdomain can be generated easily; (2) grids can be, in a sense, adapted to the solution; (3) different equation sets can be used in different zones; and, (4) this approach allows for a convenient data base organization scheme. Using this code, separated flows on a NACA 0012 section wing and on the NASA Ames WING C have been computed. First, the effects of turbulence and artificial dissipation models incorporated into the code are assessed by comparing the TNS results with other CFD codes and experiments. Then a series of flow cases is described where data are available. The computed results, including cases with shockinduced separation, are in good agreement with experimental data. Finally, some futuristic cases are presented to demonstrate the abilities of the code for massively separated cases which do not have experimental data.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 July 1986
 Bibcode:
 1986STIN...8811089K
 Keywords:

 Computer Programs;
 Euler Equations Of Motion;
 NavierStokes Equation;
 Regions;
 Separated Flow;
 Transonic Flow;
 Wings;
 Airfoils;
 Computational Grids;
 Dissipation;
 Grid Generation (Mathematics);
 Relaxation (Mechanics);
 Three Dimensional Flow;
 Topology;
 Turbulence;
 Fluid Mechanics and Heat Transfer