Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has created this Calculator and 100+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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11 Other formulas that you can solve using the same Inputs

Static Pressure behind of normal shock using normal shock momentum equation
Static pressure behind shock=Static pressure ahead of shock+(density ahead of shock*(Velocity upstream of shock^2))-(Density behind shock*(Velocity downstream of shock^2)) GO
Velocity behind of normal shock by normal shock momentum equation
Velocity downstream of shock=sqrt((Static pressure ahead of shock-Static pressure behind shock+(density ahead of shock*(Velocity upstream of shock^2)))/Density behind shock) GO
Static Pressure ahead of normal shock using normal shock momentum equation
Static pressure ahead of shock=Static pressure behind shock+(Density behind shock*(Velocity downstream of shock^2))-(density ahead of shock*(Velocity upstream of shock^2)) GO
Density ahead of normal shock using normal shock momentum equation
density ahead of shock=(Static pressure behind shock+(Density behind shock*(Velocity downstream of shock^2))-Static pressure ahead of shock)/(Velocity upstream of shock^2) GO
Density behind normal shock using normal shock momentum equation
Density behind shock=(Static pressure ahead of shock+(density ahead of shock*(Velocity upstream of shock^2))-Static pressure behind shock)/(Velocity downstream of shock^2) GO
Velocity behind a normal shock
Velocity downstream of shock=Velocity upstream of shock/((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number ahead of shock^2)))) GO
Velocity behind of normal shock from normal shock energy equation
Velocity downstream of shock=sqrt(2*(Enthalpy ahead shock+((Velocity upstream of shock^2)/2)-Enthalpy behind shock)) GO
Velocity ahead of normal shock from normal shock energy equation
Velocity upstream of shock=sqrt(2*(Enthalpy behind shock+((Velocity downstream of shock^2)/2)-Enthalpy ahead shock)) GO
Enthalpy behind of normal shock from normal shock energy equation
Enthalpy behind shock=Enthalpy ahead shock+((Velocity upstream of shock^2)-(Velocity downstream of shock^2))/2 GO
Enthalpy ahead of normal shock from normal shock energy equation
Enthalpy ahead shock=Enthalpy behind shock+((Velocity downstream of shock^2)-(Velocity upstream of shock^2))/2 GO
Prandtl Condition
Velocity downstream of shock=(Critical speed of sound^2)/Velocity upstream of shock GO

Critical speed of sound from Prandtl relation Formula

Critical speed of sound=sqrt(Velocity downstream of shock*Velocity upstream of shock)
a<sup>*</sup>=sqrt(V<sub>2</sub>*V<sub>1</sub>)
More formulas
Prandtl Condition GO
Characteristic Mach Number behind shock GO
Characteristic Mach number GO
Relation between Characteristic Mach number and Mach number GO
Mach Number behind the shock GO
Shock strength GO
Velocity behind a normal shock GO
Entropy change across normal shock GO
Static Pressure ahead of normal shock using normal shock momentum equation GO
Static Pressure behind of normal shock using normal shock momentum equation GO
Density ahead of normal shock using normal shock momentum equation GO
Density behind normal shock using normal shock momentum equation GO
Enthalpy ahead of normal shock from normal shock energy equation GO
Enthalpy behind of normal shock from normal shock energy equation GO
Velocity ahead of normal shock from normal shock energy equation GO
Velocity behind of normal shock from normal shock energy equation GO
Velocity behind of normal shock by normal shock momentum equation GO
Velocity ahead of normal shock by normal shock momentum equation GO
Velocity upstream of shock using Prandtl relation GO
Density ratio across a normal shock GO
Pressure ratio across a normal shock GO
Temperature ratio across a normal shock GO
Static enthalpy ratio across a normal shock GO
Stagnation pressure behind normal shock by Rayleigh Pitot tube formula GO
Density behind normal shock for given upstream density and Mach number GO
Static pressure behind normal shock for given upstream pressure and Mach number GO
Static temperature behind normal shock for given upstream temperature and Mach number GO
Static enthalpy behind normal shock for given upstream enthalpy and Mach number GO

What is Prandtl relation?

Prandtl relation is an intermediate relation for normal shocks. It relates the velocity ahead of a shock to the downstream velocity after the shock, which in turn help to obtain downstream Mach number of the flow.

How to Calculate Critical speed of sound from Prandtl relation?

Critical speed of sound from Prandtl relation calculator uses Critical speed of sound=sqrt(Velocity downstream of shock*Velocity upstream of shock) to calculate the Critical speed of sound, Critical speed of sound from Prandtl relation formula is defined as the square root of product of upstream and downstream velocities across the normal shock. Critical speed of sound and is denoted by a* symbol.

How to calculate Critical speed of sound from Prandtl relation using this online calculator? To use this online calculator for Critical speed of sound from Prandtl relation, enter Velocity downstream of shock (V2) and Velocity upstream of shock (V1) and hit the calculate button. Here is how the Critical speed of sound from Prandtl relation calculation can be explained with given input values -> 254558.4 = sqrt(50*100).

FAQ

What is Critical speed of sound from Prandtl relation?
Critical speed of sound from Prandtl relation formula is defined as the square root of product of upstream and downstream velocities across the normal shock and is represented as a*=sqrt(V2*V1) or Critical speed of sound=sqrt(Velocity downstream of shock*Velocity upstream of shock). Velocity downstream of shock is the velocity of flow behind the shock wave and Velocity upstream of shock is the velocity of flow ahead of the shock wave.
How to calculate Critical speed of sound from Prandtl relation?
Critical speed of sound from Prandtl relation formula is defined as the square root of product of upstream and downstream velocities across the normal shock is calculated using Critical speed of sound=sqrt(Velocity downstream of shock*Velocity upstream of shock). To calculate Critical speed of sound from Prandtl relation, you need Velocity downstream of shock (V2) and Velocity upstream of shock (V1). With our tool, you need to enter the respective value for Velocity downstream of shock and Velocity upstream of shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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