Abstract:
An aeroelastic prediction framework in MATLAB with modularity in the quasi-steady aerodynamic methodology is
developed. Local piston theory (LPT) is integrated with quasi-steady methods including shock-expansion theory and
the Supersonic Hypersonic Arbitrary Body Program (SHABP) as a computationally inexpensive aerodynamic solver.
Structural analysis is performed using bilinear Mindlin-Reissner quadrilateral plate elements. Strong coupling of the
full-order system and linearization of the modal-order system are implemented. The methodology is validated against
published experimental data in literature and benchmarked against Euler computation in the Edge CFD code. The
flutter dynamic pressure is predicted to within 10% of the experimental value for 140 times lower computational cost
compared to CFD. Good agreement in other cases is obtained with the industry-standard ZONA7 and ZONA7U codes.
