| Title |
Accuracy of aerodynamically and structurally non-linear unsteady vortex lattice method for aeroelastic prediction in low-Reynolds flows |
| Authors |
Dagilis, Mindaugas ; Lendraitis, Martynas ; Kilikevičius, Sigitas |
| DOI |
10.3390/aerospace13080661 |
| Full Text |
|
| Is Part of |
Aerospace.. Basel : MDPI. 2026, vol. 13, iss. 8, art. no. 661, p. 1-16.. ISSN 2226-4310 |
| Keywords [eng] |
vortex lattice method ; non-linear aeroelasticity ; flutter ; wind tunnel experiment |
| Abstract [eng] |
Panel-based aeroelasticity models are commonly used to conduct mid-fidelity aeroelastic analysis. The unsteady vortex lattice method (UVLM) in particular is used when non-linear aerodynamic corrections are needed, for example by utilizing the α-convergence method. While this method is well tested for non-linear corrections in high-Reynolds transonic flows for both steady and unsteady cases, its effectiveness has not been well researched in unsteady low-Reynolds flows. This paper tests the effectiveness of the α-convergence method in this regime by comparing modeling results with original wind tunnel test results. In the steady aeroelastic displacement tests, the aerodynamic non-linearity improved the modeling results significantly, with an error under ±10% at all tested angles of attack, compared to a maximum error of −30.8% for the aerodynamically linear models. In the flutter test case, the aerodynamic non-linearity had less of an impact, with structural non-linearity being more important in this case. However, the maximum flutter speed error for the aerodynamically non-linear model was still lower, at −14.4%, compared to +19.6% for the aerodynamically linear model. |
| Published |
Basel : MDPI |
| Type |
Journal article |
| Language |
English |
| Publication date |
2026 |
| CC license |
|
