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Table 2

Objective function, design variables, and parameters of the flutter optimization problem.

Objective function Type
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 °
Parameters Value

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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