Normal Shock Wave Modules

Calculate compressible flow normal shock wave properties for an ideal gas.

The flow is assumed to be supersonic upstream of the shock wave (M > 1), and subsonic downstream of the shock wave (M < 1). The shock wave is assumed to be adiabatic and non isentropic. Phase changes are ignored.

Reference : Fluid Mechanics, Frank M White, McGraw Hill

Change Module :

• Compressible Flow Area And Internal Diameter Calculation Module
• Compressible Flow Blowdown Time Calculation Module
• Compressible Flow Calculation Module
• Compressible Flow Critical Flow Calculation Module
• Compressible Flow Fanno Line Calculation Module
• Compressible Flow Gas Property Calculation Module
• Compressible Flow Minor Loss Factor Calculation Module
• Compressible Flow Nozzle Flow Rate Calculation Module
• Compressible Flow Pitot Tube Calculation Module
• Compressible Flow Pressure Loss Factor Calculation Module
• Compressible Flow Pressure Relief Valve Calculation Module
• Compressible Flow Pressure Relief Vent Calculation Module
• Compressible Flow Speed Of Sound Calculation Module
• All

Related Modules :

• API 520 Pressure Relief Device Calculation Module
• Fluid Density And Volume Calculation Module
• Gas Compressibility Factor Calculation Module
• IAPWS R7-97 Steam Table Calculation Module
• Line Pipe Cross Section Calculation Module
• More Normal Shock Wave Modules