The present work is concerned with the study of transitional flows over aerospace configurations. The work is conducted with an in-house CFD code which has transition prediction capabilities brought through the use of the γ− Reθ transition model. The code solves the RANS equations in a fully coupled fashion with the turbulent and transition transport equations. Four aerospace applications are selected including two-dimensional (2-D) and three-dimensional (3-D) test cases. The 2-D cases are airfoil configurations in which the viscous relations can be strongly affected by the transitional behavior of the flow. The 3-D case includes a launch vehicle configuration at a supersonic flow condition which was studied in past work. In general, good agreement with experimental results is obtained for the 2-D test cases. For the 3-D configuration, the use of transition formulation provided significant improvement in the correlation with experimental data and it has also contributed to a better understanding of the flow phenomena in this rocket-type configuration.