The static pressure at the nozzle throat where the flow is sonic, denoted as p1*, refers to the pressure of the fluid or gas at the point within the nozzle 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 nozzles and supersonic or hypersonic aircraft engines.
- Static pressure at the nozzle of sonic flow (p1*) in N/m^2
- Total pressure at the nozzle (p0,1) in N/m^2
- Specific heat ratio (𝛾)