Pipeng Toolbox : Supersonic Pitot Tube Calculators Blank User
Short Cuts
GO
Main ±
Beams ±
References ±
Fluid Flow ±
Fluid Properties ±
Maths ±
Materials ±
Pipelines ±
Soils ±
Subsea ±
Demo

Compressible Flow Pitot Tube

Calculate compressible flow velocity from Pitot tube temperature and pressure for subsonic and supersonic flow.

The flow velocity can be calculated from the staganation pressure, static pressure and temperature. For supersonic flow a shock wave forms in front of the Pitot tube, and the pressure and temperature measurements must be compensated. The upstream and downstream flow is assumed to be isentropic. The shock wave is adiabatic and non isentropic.

Reference : Fluid Mechanics, Frank M White, McGraw Hill

Change Module :

Related Modules :

[FREE] tools are free in basic mode with no login (no plots, tables, goal seek etc). Login or Open a free account to use the tools in plus mode (with plots, tables, goal seek etc).
[PLUS] tools are free in basic CHECK mode with Login or Open a free account (CHECK values no plots, tables, goal seek etc). Buy a Subscription to use the tools in plus mode (with plots, tables, goal seek etc).
Try plus mode using the Plus Mode Demo tools with no login.   Help Using The Pipeng Toolbox (opens in the popup workbook)

Links : ±
CALCULATOR : Compressible Flow Gas Density And Compressibility Factor [FREE]   ±

Calculate gas compressibility factor and density from gas temperature and pressure for common gases: argon Ar, n-decane C10H22, ethylene C2H4, ethyl chloride C2H5Cl, ethane C2H6, propene C3H6, propane C3H8, iso-butane C4H10, n-butane C4H10, iso-pentane C5H12, n-pentane C5H12, n-hexane C6H14, n-heptane C7H16, n-octane C8H18, n-nonane C9H20, methyl chloride CH3Cl, methane CH4, chlorine Cl2, carbon monoxide CO, carbon dioxide CO2, hydrogen H2, steam H2O, hydrogen sulphide H2S, hydrogen chloride HCl, helium He, krypton Kr, nitrogen N2, air N2+O2, ammonia NH3, oxygen O2, sulphur dioxide SO2, xenon Xe.

The gas compressibility factor is calculated from the critical point temperature, critical point temperature, and the accentric factor using either the Peng Robinson, Soave, Redlich Kwong or Van Der Waals equations of state (EOS). The compressibility factor calculation is valid for gas phase only. Use the Result Plot option to plot compressibility factor versus pressure and temperature, compressibility factor versus pressure and equation of state type, or compressibility factor versus temperature and equation of state type.

Tool Input

  • fluidtype : Fluid Type
    • Pcu : User Defined Critical Point Pressure
    • Tcu : User Defined Critical Point Temperature
    • ωu : User Defined Accentric Factor
    • SGu : User Defined Gas Specific Gravity
  • eostype : Equation Of State Type
    • Zu : User Defined Gas Compressibility Factor
  • P : Fluid Pressure
  • T : Fluid Temperature

Tool Output

  • ρ : Fluid Density
  • ω : Accentric Factor
  • Pc : Critical Point Pressure
  • Rg : Specific Gas Constant
  • SG : Gas Specific Gravity
  • Tc : Critical Point Temperature
  • Vm : Molar Volume
  • Z : Compressibility Factor
  • cvg : Convergence Check
  • mmg : Gas Molar Mass

CALCULATOR : Compressible Flow Pitot Static Tube Mach Number From Pressure [FREE]   ±

Calculate Mach number and flow velocity from Pitot tube pressure measurements.

For subsonic and supersonic flow the Mach number can be calculated from the upstream or flowing pressure. The speed of sound and velocity can be calculated from either the upstream temperature, or the stagnation temperature measured at the tip of the Pitot tube.

For supersonic flow a normal shock wave forms in front of the Pitot tube. The Mach number and velocity can also be calculated from the downstream pressure and temperature. The downstream pressure and temperature option should not be used for subsonic flow.

The flow is assumed to be adiabatic for an ideal gas. The flow is isentropic for subsonic conditions, and non isentropic for supersonic conditions. The shock wave is non isentropic.

Tool Input

  • fluidtype : Fluid Type
    • γu : User Defined Specific Heat Ratio
    • SGu : User Defined Gas Specific Gravity
  • zfactype : Factor Type
    • Zu : User Defined Compressibility Factor
  • temptype : Measured Temperature Type
    • Tou : User Defined Stagnation Temperature
    • Tdu : User Defined Downstream Temperature
  • flowtype : Subsonic Or Supersonic Flow
  • Po : Pitot Tube Downstream Stagnation Pressure
  • Pd : Pitot Tube Downstream Static Pressure

Tool Output

  • γ : Specific Heat Ratio
  • ρd : Downstream Density
  • ρu : Upstream Density
  • Cd : Downstream Speed Of Sound
  • Cu : Upstream Speed Of Sound
  • Md : Downstream Mach Number
  • Mu : Upstream Mach Number
  • Pu : Upstream Pressure
  • Rg : Specific Gas Constant
  • SG : Gas Specific Gravity
  • Td : Downstream Temperature
  • To : Stagnation Temperature
  • Tu : Upstream Temperature
  • Vd : Downstream Velocity
  • Vu : Upstream Velocity
  • Z : Compressibility Factor
  • mmg : Gas Molar Mass