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 includes flutter prediction for this configuration at a Mach number of M∞ = 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.

Duke Scholars

Author Jeffrey P. Thomas Thomas Lord Department of Mechanical Engineering and Materia ...

Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...