Christopher S. Talley, Timothy J. Wray, Yi Wang, Sami D. Habchi

DOI Number: N/A

Conference number: IFASD-2019-101

This paper presents a procedure for the simulation of dynamic aeroelastic responses at varying flight conditions. These predictions were done in real-time using aeroelastic reduced-order models (ROMs). Aeroelastic ROMs were generated over a course flight envelope of varying Mach number (M=0.5, 0.6, 0.7, 0.8, 0.9, 1.0, 1.1) and angle of attack (α=0, 5, 10, 15). The NASA FUN3D computational fluid dynamics solver was used to generate high fidelity training and verification data. The Python toolbox SIPPY was used for state-space system identification. Once ROMs at several angles of attack and Mach numbers were generated, a ROM interpolation scheme was used to simulate the aerodynamic response at an arbitrary flight condition. The ROM responses agree very well with CFD verification data. The computed flutter buckets at non-zero angle of attack for Euler and RANS solutions were compared.

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In Categories: Computational Aeroelasticity, IFASD 2019
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