Momentum integral method at the beginning of crossflow development
Abstract
The necessity of choosing crossflow profiles which satisfy a compatibility condition is demonstrated for eliminating problems at the transition point in switching from twodimensional to threedimensional numerical calculations. Equations are developed for threedimensional boundary layers and solutions are expressed in terms of integral thicknesses. The constraints imposed on the transition from two to threedimensional flow simulations involve approximating the crossflow values close to zero. Furthermore, the estimation of the boundary layer thickness for streamwise and crosswise profiles is considered, which alters the values for the momentum thicknesses for the horizontal and vertical velocities, but also permits solving for accelerating and crossflow profiles.
 Publication:

AIAA Journal
 Pub Date:
 April 1982
 DOI:
 10.2514/3.7928
 Bibcode:
 1982AIAAJ..20..556M
 Keywords:

 Boundary Layer Transition;
 Computational Fluid Dynamics;
 Cross Flow;
 Flow Distribution;
 Integral Equations;
 Laminar Boundary Layer;
 Three Dimensional Boundary Layer;
 Aircraft Parts;
 Flow Velocity;
 Two Dimensional Flow;
 Wings;
 Fluid Mechanics and Heat Transfer