The static pressure at the diffuser throat where the flow is sonic, denoted as p2*, refers to the pressure of the fluid or gas at the point within the diffuser where the flow velocity reaches the speed of sound (Mach 1). This pressure is a critical parameter in fluid dynamics, particularly in compressible flow situations such as those encountered in rocket propulsion systems, supersonic or hypersonic aircraft engines, and other high-speed flow applications.
- Static pressure at the diffuser (p2*) in N/m^2
- Total pressure at the diffuser (p0,2) in N/m^2
- Specific heat ratio (𝛾)