Correction
Aerodynamic Benefits of Camber Morphing Technology for Strut-Braced Wing Configurations (American Institute of Aeronautics and Astronautics Inc, AIAA)
I. Tsatsas (TU Delft - Group De Breuker, TU Delft - Arts & Crafts)
E. Sticchi (TU Delft - Wind Energy)
X. Córcoles (TU Delft - Group Sodja)
Roeland de Breuker (TU Delft - Aerospace Structures & Materials)
Jurij Sodja (TU Delft - Group Sodja)
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Abstract
Correction notice The CL in the title of Fig. 7(b) was corrected from 0.4 in the original version to CL=1.0. (a) Climb local lift spanwise distribution at CL=1 0 0.2 0.4 0.6 0.8 1 0 5 10 10-3 0 0.2 0.4 0.6 0.8 1 0 5 10 10-3 (b) Solid line (suction side)-dashed line (pressure side) Fig. 7 Local lift coefficient distribution with a selected friction coefficient of one section.