Abstract
The unsteady aerodynamic characteristics of an F18 aircraft performing harmonic oscillatory maneuvers in pitch are presented and analyzed in this paper. The wind-tunnel tests using the Dynamic Plunge-Pitch-Roll model mount at Virginia Tech Stability Wind Tunnel are first described, and the data reduction techniques are discussed. The typical experimental results are then illustrated, and the resulting hysteresis loops analyzed. Based on the observation that all the hysteresis loops with same nondimensional maximum pitch rate (qmax) are tangential to one another at both top and bottom of these loops at current flow conditions, qmax is used as a nondimensional quantity in characterizing these harmonic oscillatory motions. Finally, a state-space model is identified to describe the unsteady aerodynamic characteristics on the basis of the data obtained. The performance and prediction capability of this model are demonstrated through several examples. The dynamic properties of this model are also discussed.
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