1. i n the last tm to three years (refs. 1-31. Most Of the research effort has concentrated on modeling the flow over wings and wing/body configurations, assuming t h d t these bodies are i n free air. However, the experimental data with which comparisons are made dre taken inside wind tunnels where wall-interference effects can be substantial (refs. 4-51, particularly in the case of solid tunnel walls. The use of wind tunnc 1.s which contain ventilated and/or adaptive walls can reduce these interference effects dramatically and provide data Which are Dearer to free-stream quality. The validity of data obtained i n such tunnels for verifying numerical schemes is then improved, but may S t i l l Contain interference effects. scheme has been tested extensively for high-Reynolds-number viscous flows over wings and prolate spheroids by Vatsa (ref. 81 and vatsa, Thomas, and Wedan (ref. 9). In the present effort, the wing-alone ccde lref. 8) has been modified to accommodate the wind-tunnel walls as the outer boundary, with appropriate inflow and outflow boundary conditions.
2. The contravariant velocity components used in a s . 131-17) are defined as: u = c u + 5 v t 5 w