Aeroelastic stability prediction is critical to the successful design, development, and flight testing of rotorcraft. As configurations reach higher speeds, new challenges in high Mach number unsteady aerodynamic modeling need to be addressed, especially for higher frequency aeroelastic modes with significant coupling. In this paper, linear unsteady aerodynamics and Leishman–Beddoes attached flow models are applied and compared to two-dimensional (2D) computational fluid dynamics (CFD) (airfoil) and three-dimensional (3D) computational fluid dynamics/computational structural dynamics (CFD/CSD) (rotor) analysis for operating conditions of interest. The Leishman–Beddoes model demonstrates improved agreement with CFD data. In the 2D assessment, the rotorcraft comprehensive analysis system (RCAS) is used to simulate a representative airfoil undergoing prescribed pitch and heave oscillations. CFD results are presented to compare each model (linear unsteady and Leishman–Beddoes). In the 3D assessment, a full rotor CFD/CSD test case is evaluated for aeroelastic stability and compared to the RCAS standalone analysis. The RCAS rotor structural model is coupled with the HELIOS CFD code, and a swashplate cyclic pitch input is used to excite a lightly damped rotor mode. The transient response based on RCAS–HELIOS is compared to the standalone RCAS result for both linear unsteady and Leishman–Beddoes unsteady aerodynamics. This study demonstrates that the Leishman–Beddoes model can produce similar stability results to the computationally expensive coupled CFD/CSD approach of RCAS–HELIOS, but at a lower computational cost, for high-speed axial flow conditions.
Buccio et al. (Thu,) studied this question.