This study used a NACA 6409 smooth wing section. Its performance is compared to an enhanced design incorporating revolving cylinder on the upper airfoil surface. The boundary conditions for present work were Reynolds (105), and attack angles (0,2,4,6,8,10,12,14,16). A turbulence model was developed (SST K-), one of aerodynamics models. well-suited sensing flow near wall. evaluated at three posi...

Despite its desire to achieve cognitive dominance for multi-domain operations, the Army has yet develop fully and adopt concept of performance enhancement. This article provides a comprehensive assessment Army’s efforts in this area, explores increasing demands on soldier cognition, compares current approach adversaries. Its conclusions will help US military policy practitioners establish cultu...