Leading-edge slat optimization for maximum airfoil lift
Lawrence E. Olson, Phillip R. McGowan, Clayton J. Guest, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Ames Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979 - Technology & Engineering - 23 pages
1 page matching boundary-layer coordinate system in this book
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80-Foot Wind Tunnel adverse pressure gradient aerodynamic analysis aerodynamic calculation AIAA Ames 40 Ames Research Center angle of attack attached flow boundary-layer coordinate system boundary-layer equations Cebeci Computer Sciences Corporation configurations confluent boundary layer constrained function minimization constraint coupling potential flow determining the position eddy viscosity Effect of slat experimentally optimized slat Figure finite-difference flow and boundary-layer flow field high-lift incipient flow separation iteratively coupling potential laminar instability LEADING-EDGE SLAT OPTIMIZATION lift coefficient main airfoil main element maximizes the lift MAXIMUM AIRFOIL LIFT measured maximum lift Methods in Appl minimizes the suction Moffett Field multielement airfoils NASA numerical procedure OPTIMIZATION FOR MAXIMUM optimized slat position position for maximum position that minimizes prediction of incipient pressure distributions Reynolds stress single-slotted flap skin friction slat deflection slat location slat wake suction peak Swept Wings THEORETICAL METHOD theoretical predictions theoretically optimized Vanderplaats Viscous/Potential Flow wind-tunnel testing wing maximum lift xs/c ys/c