3DOF problem - original report from VZLU/ARTI

Mathematical Model

• RANS + Spalart Allmaras turbulence model
• 3DOF linear model
• continuous transformation of the airfoil surface is performed

Eigenfrequencies of structure model

Continuous transformation of surface

Figures

Parameters

airfoil weight=                         0.086622        ;[kg]
airfoil stiffness=                      105.109         ;[N/m]
airfoil torsional stiffness=            3.695582        ;[N m/rad]
airfoil flap stiffness     =            0.025           ;[N /rad] ??? jednotky

airfoil torsional static moment=        -7.796e-4       ;[kg m]
airfoil torsional inertia moment=       4.8729e-4        ;[kg m^2]

flap torsional static moment=           0.0;
flap torsional inertia moment=          1e-6; [kg m^2]

damping of airfoil bending=             0;
damping of airfoil torsion=             0;
damping of flap torsion=                0;

x flap location=                        0.8     ; 

U=12 m/s

U=17 m/s

U=22 m/s

U=27 m/s

U=32 m/s