This paper focus on the assessment of aerodynamic forces applied on an
aircraft. First, numerical analysis is performed on a simplified linear
two-degree-of-freedom (2DOF) airfoil system model. Methods of aerodynamic
force determination are established at different airspeed conditions and the
calculated dynamic forces correlated well to the actual forces. Next, a finite
element model of the airfoil is developed to represent its structural dynamics, and
the established force determination methods are applied to determine the
aerodynamic forces acting on such model. After that, a physical downsizing model
of the airfoil is manufactured and its natural frequencies, damping ratios, and mode
shapes are calculated and compared to those obtained from the analytical models.
Vibration experiments are also conducted to measure the physical model’s
structural response in the wind tunnel, and its aerodynamic forces are calculated
based on the data recorded by the attached accelerometers.
Keywords: Aircraft wing model, Experimental measurement, Force
determination methods, Frequency response function, Multiple-degree-offreedom
system, Vibratory force and moment.
