Objective function, design variables, and parameters of the flutter optimization problem.
|Square of error between aerodynamic matrices||∥[Ăhr](Xar, κ1f, Mr)||Minimization|
|Design Variables||Baseline Value|
|Chord at root section||cr||12.10 m|
|Chord at break section||cb||7.26 m|
|Chord at tip section||ct||2.73 m|
|Wing sweep||Λ||37.16 °|
|Mach number of the reference geometry||Mr||0.8|
|Mach number of the scaled model wing||Mm||0.3|
|Reduced frequency of the first flutter mode||κ1||0.183|
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