Subsonic flow in a corner
Abstract
Laminar and turbulent flow, as found e.g., at the wingfuselage junction, were studied numerically. In laminar flow a vortical system close to the edge disturbs calculations. Modifications to the field of the secondary velocity improve this. Further improvement can be achieved by varying vortex parameters. In the turbulent mode, the anisotropy of the turbulence should be considered in the calculation of the second order vortices, (although here it was ignored, and qualitatively correct results are still obtained). The basic equations are the streamwise momentum equation, the streamwise component of the vorticity equation, and two Poissontype equations for secondary velocities.
 Publication:

In its La Rech. Aerospatiale
 Pub Date:
 September 1981
 Bibcode:
 1981ReAeB.......45A
 Keywords:

 BodyWing Configurations;
 Corner Flow;
 Laminar Flow;
 Numerical Flow Visualization;
 Turbulent Flow;
 Anisotropy;
 Flow Velocity;
 NavierStokes Equation;
 Poisson Equation;
 Secondary Flow;
 Three Dimensional Flow;
 Vortices;
 Fluid Mechanics and Heat Transfer