Two-Dimensional Aeroelastic Limit Cycle Oscillation Computations for the NASA Benchmark Supercritical Wing Configuration

Aeroelastic flutter onset and limit cycle oscillation results are computed for a two-dimensional model of the NASA benchmark supercritical wing configuration consisting of the NASA SC(2)-0414 airfoil section. The purpose of this investigation is to contribute to the objectives of the NASA Fourth Aeroelastic Prediction Workshop (AePW-4) High Angle Working Group, which include flutter prediction for this configuration at a Mach number of 0.8 and wind-off angles-of-attack ranging from zero to six degrees. This study also aims to determine the sensitivity of the aeroelastic results to various model parameters, which will help inform and guide a new round of wind experiments for the configuration planned for later this year.