Static pressure at the nozzle where the flow is sonic Calculator

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)

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