Aeroelastic Calculations for the Hawk Aircraft Using the
M.A. Woodgate, K.J. Badcock, A.M. Rampurawala, B.E. Richards, D.Nardini & M. J. deC Henshaw
This paper demonstrates coupled time domain computational fluid dynamics and computational
structural dynamics simulations for flutter analysis of a real aircraft in the transonic regime.
It is shown that a major consideration for a certain class of structural models is the transformation
method which is used to pass information between the fluid and structural grids. The aircraft used
for the calculations is the BAE SYSTEMS Hawk. The structural model, which has been developed
by BAE SYSTEMS for linear flutter calculations, has only O(10) degrees of freedom. There is
therefore a significant mismatch between this and the surface grid on which loads and deflections
are defined in the CFD calculation. This paper extends the Constant Volume Tetrahedron tranformation,
previously demonstrated for wing-only aeroelastic calculations, to multi-component, or
full aircraft, cases and demonstrates this for the Hawk aircraft. A comparison is made with the
predictions of a BAE SYSTEMS linear flutter code.
Reference: M.A. Woodgate, K.J. Badcock, A.M. Rampurawala, B.E. Richards, D.Nardini & M. J. deC Henshaw (2005). Aeroelastic Calculations for the Hawk Aircraft Using the Euler Equations. Journall of Aircraft 42 No, 4. doi: 10.2514/1.5608 © . Reproduced with permission.