A simulation environment has been developed enabling the computation of the elastic and trimmed aircraft. It consists of a trim algorithm which is coupled with a procedure to account for the interaction between fluid and structure. The trim algorithm is based on a Newton method with a discretized Jacobian. It incorporates the six degrees of freedom (DoF) flight-mechanics equations and thereby enables to compute different trimmed states. The fluid-structure interaction (FSI) procedure uses a partitioned approach to compute the flow around the configuration in static aeroelastic equilibrium. This simulation environment has been successfully applied to trim a rigid transportaircraft configuration in viscous flow as well as in inviscid flow with rigid and flexible wing.


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    Wing Divergence of Trimmed Aircraft

    T. Niblett | NTIS | 1986


    Wing Divergence of Trimmed Aircraft

    L. T. Niblett | NTIS | 1987



    Trimmed CFD Simulation of a Complete Helicopter Configuration

    Khier, W. / Dietz, M. / Schwarz, T. et al. | British Library Conference Proceedings | 2007