This paper presents the preliminary results of a research investigation intended to identify the most appropriate compressibility correction approach for the Flamelet Progress/Variable (FPV) formulation. This topic is vital for the design and advancement of hypersonic airbreathing vehicles. Consequently, there is a high demand for accurate, versatile, and computationally cost-effective methods for simulating supersonic combustion. This paper discusses the Flamelet Progress/Variable (FPV) formulation, which was utilized to simulate a reacting jet injection in a supersonic crossflow. The preliminary results presented in this paper are intended to show that the FPV formulation has been implemented in a well-established computational fluid dynamics (CFD) code. Additionally, we observed that the procedure to ignite the flow field in a FPV formulation is not trivial, and should be given more attention.