The analyses presented in this paper are focus on the solution of cases 1 and 3A proposed by the second Aeroelastic Prediction Workshop , using an open-source CFD code. The reference cases presented by AePW-2 analyze the transonic flow around a Benchmark Supercritical Wing (BSCW). AePW-2 Test case 1 consists of a forced oscillation problem with Mach number of 0.7 and angle of attack of 3 deg, while AePW-2 Test case 3A analyzes a flow with Mach number of 0.85 and angle of attack of 5 deg, being that an unforced and unsteady problem. In the study, we simulated both test cases using the software SU2, being the results validated by comparison with experimental data provided by AePW-2. The results matched with accuracy with the experimental data and presented a good response for the analyses of AePW-2 test case 3A, proving the software capability of capture the physical phenomena involved in this type of flow.