Abstract
A model for the lift force of an aircraft operating at high angles of attack is presented. In this model the unsteady aerodynamic effect is expressed as a dependence, of the lift on an internal variable for which a differential equation is postulated. The resulting model is applied to a delta wing subjected to forced pitching moment oscillations. The unknown parameters representing the unsteady aerodynamics are estimated by nonlinear and linear least squares procedures from wind tunnel data at three different frequencies and the angle of attack between 30 and 60 deg. The predicted aerodynamic terms in the model agree well with measured data.
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