Dynamic Aeroelastic Simulations of the Pazy Wing by UVLM with Nonlinear Viscous Corrections

Free Wake Panel Method Simulations of a Highly Flexible Wing in Flutter and Gusts

“…The first flutter mode LCO frequency for the Pazy wing shows little variation with α and U ∞ (Drachinsky et al, 2022) and is between 25 and 30 Hz. Previous simulations (Ritter and Hilger, 2022) found a similar range, between 31 and 33 Hz. Our current results indicate LCO at 28.5 Hz, while the experiments show around 28.3 Hz at α = 3 • and U ∞ = 50 m/s, making this an excellent agreement, within under 1%.…”

“…In order to validate such models, the Pazy wing experiment (Avin et al, 2022) was conducted as part of the Aeroelastic Prediction Workshop (AePW) Large Deflection Working Group (Ritter and Hilger, 2022;Drachinsky et al, 2022;Riso and Cesnik, 2023). The Pazy wing was created at Technion with the intent to be used for validation of aeroelastic models.…”

“…Aircraft wings have become more flexible in recent years, mostly due to high aspect ratio wings having favorable aerodynamic properties (such as lower induced drag) and lightweight structures helping improve fuel efficiency, but also because the flexibility of the wings can also have advantages for the dynamic response of the aircraft (Ritter and Hilger, 2022). These factors have led to the very flexible wings that are present in modern commercial aircraft such as the Boeing 787 and in high-altitude long-endurance drones.…”

Free Wake Panel Method Simulations of a Highly Flexible Wing at Flutter

“…Models that can accurately include the large deflections into stability calculations of these aircraft are needed to avoid late stage failures in the development cycle. In order to validate such models, the Pazy wing experiment [1] was conducted as part of the Aeroelastic Prediction Workshop (AePW) Large Deflection Working Group [2][3][4]. This is a simple, yet challenging test case, as the non-linearities have substantial effects on the structural and aeroelastic properties of the wing, with "some trends that are opposite to those obtained in the linear domain" [5].…”

Aerodynamic and Static Coupling Simulations of the Pazy Wing with Transitional CFD for the Third Aeroelastic Prediction Workshop

“…Aeroelastic simulations (static coupling and flutter) that have been presented in the LDWG to analyze the behavior of the Pazy Wing are based on geometrically nonlinear structural methods -which are indispensable for this test caseand linear (potential) aerodynamics, mostly the UVLM and the DLM are applied. This combination offers advantages such as low computational cost, and even aerodynamic nonlinearities -due to stall, for instance -can be modeled by simple approaches [2][3][4]. These methods enable the evaluation of the stability boundary of the Pazy Wing which strongly depends on the combination of airspeed and static angle of attack due to the large structural deflections and the corresponding changes in the eigenvalues and mode shapes of the wing.…”