Steady and unsteady aeroelastic computations of HIRENASD wing for low and high Reynolds numbers

We perform static and dynamic aeroelastic analyses of the HIRENASD wing based on NASA's reference data delivered for two test cases with different ight conditions. The tests have been conducted in cryogenic medium to investigate steady and unsteady aeroelastic responses in transonic regime for low and high Reynolds numbers. For computational studies, the latest structural model of NASA is used. First, a free vibration analysis is performed in Nastran. Then, the modal solution is imported from the finite element solver to ZEUS, where the aerodynamic model and uid structure interaction parameters are constructed. Steady and unsteady aeroelastic results are examined for the specified stations along the wing span, and interpolated for chordwise direction so as to match them with the wind tunnel test points. The designated output parameters such as steady aerodynamic lift, moment and drag coefficients, and steady and unsteady pressure distributions along the chordwise direction are compared to the experimental results.