22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.5.3

PREDICTION OF AERODYNAMIC - LIFT REDISTRIBUTION ON FLEXIBLE WING STRUCTURE USING TRANSONIC UNSTEADY AERODYNAMIC CODE - NTRANS

I. W. Tjatra, M. Kadar, D. Rahmawati
Institute of Technology Bandung, Bandung 40132 , Indonesia

Keywords: lift prediction, flexible wing, transonic unsteady aerodynamics, computational

Aeroelastic analysis of lifting surface involves solving fluid and structural equations together. Such coupling procedure need an advanced computational structure mechanics for the development of structural model and advanced computational fluid dynamics for the solution of aerodynamics flow model. NASTRAN, a well known computer code for structural analysis, has an advanced structural modeling, but does not has the capability for solving aerodynamically nonlinear problems, such as aeroelasticity in transonic flow regimes. A computationally efficient technique for the prediction of aerodynamic lift redistribution on flexible wing structure in transonic flow field is presented in this paper. The advance capability in structural modelling of finite element based software module is integrated with a newly developed NTRANS, unsteady transonic aerodynamic software module. This integration is carried out through a quasi - steady coupling of the aerodynamic generalized forces with the elastic structural deformation. This integration technique has been validated for clean wing configuration. Comparison of numerical results with results obtained using other numerical technique proves that this technique is accurate and efficient for routine application.

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