Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has created this Calculator and 100+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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11 Other formulas that you can solve using the same Inputs

Isentropic temperature 1 given specific volume
Isentropic temperature 1 given specific volume=Temperature of surface 2/(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO
Isentropic temperature 2 given specific volume
Isentropic temperature 2 given specific volume=Temperature of surface 1*(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO
Isentropic temperature 2 given pressure ratio
Isentropic temperature 2 given pressure ratio=Temperature of surface 1*(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO
Isentropic temperature 1 given pressure ratio
Isentropic temperature 1 given pressure ratio=Temperature of surface 2/(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO
Temperature Ratio when Isentropic Specific Volume is Given
Temperature ratio isentropic specific volume=(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO
Isentropic Pressure at point 2
Isentropic Pressure at point 2 =pressure 1*(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO
Isentropic Pressure at point 1
Isentropic Pressure at point 1=pressure 2/(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO
Pressure Ratio in Isentropic Process
Pressure ratio isentropic process=(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO
Temperature Ratio When Isentropic Pressure is Given
Temperature ratio isentropic pressure=(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO
Deflection angle
deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) GO
Relation between Characteristic Mach number and Mach number
Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 GO

4 Other formulas that calculate the same Output

Density behind oblique shock for given upstream density & normal upstream Mach no.
Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific heat ratio-1)*(Component of upstream mach normal to oblique shock^2)))) GO
Density before the shock formation for expansion wave
Density behind shock=Stagnation pressure ahead of shock/(1-((Specific Heat Ratio-1)/2)*(Normal velocity/Old speed of sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-Time)) GO
Density before shock formation for compression wave
Density behind shock=Stagnation pressure ahead of shock/(1+((Specific Heat Ratio-1)/2)*(Normal velocity/Old speed of sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-Time)) 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

Density behind normal shock for given upstream density and Mach number Formula

Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2))))
ρ <sub>2</sub>=ρ <sub>1</sub>*((κ+1)*(M<sub>1</sub>^2)/(2+((κ-1)*(M<sub>1</sub>^2))))
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
Critical speed of sound from 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
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

How to obtain density ratio across normal shock?

Density ratio across the normal shock is obtained by rearranging the continuity equation and using Prandtl relation.

How to Calculate Density behind normal shock for given upstream density and Mach number?

Density behind normal shock for given upstream density and Mach number calculator uses Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2)))) to calculate the Density behind shock, Density behind normal shock for given upstream density and Mach number formula is defined as the product of density ratio across the normal shock and density ahead of the shock. Density behind shock and is denoted by ρ 2 symbol.

How to calculate Density behind normal shock for given upstream density and Mach number using this online calculator? To use this online calculator for Density behind normal shock for given upstream density and Mach number, enter density ahead of shock 1), Specific heat ratio (κ) and Mach Number ahead of shock (M1) and hit the calculate button. Here is how the Density behind normal shock for given upstream density and Mach number calculation can be explained with given input values -> 1.86694 = 1*((1.392758+1)*(1.5^2)/(2+((1.392758-1)*(1.5^2)))).

FAQ

What is Density behind normal shock for given upstream density and Mach number?
Density behind normal shock for given upstream density and Mach number formula is defined as the product of density ratio across the normal shock and density ahead of the shock and is represented as ρ 21*((κ+1)*(M1^2)/(2+((κ-1)*(M1^2)))) or Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2)))). density ahead of shock is the density of the fluid in the upstream direction of shock, The Specific heat ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume and Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred .
How to calculate Density behind normal shock for given upstream density and Mach number?
Density behind normal shock for given upstream density and Mach number formula is defined as the product of density ratio across the normal shock and density ahead of the shock is calculated using Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2)))). To calculate Density behind normal shock for given upstream density and Mach number, you need density ahead of shock 1), Specific heat ratio (κ) and Mach Number ahead of shock (M1). With our tool, you need to enter the respective value for density ahead of shock, Specific heat ratio and Mach Number ahead of shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Density behind shock?
In this formula, Density behind shock uses density ahead of shock, Specific heat ratio and Mach Number ahead of shock. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • 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)
  • Density behind shock=density ahead of shock*((Specific heat ratio+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific heat ratio-1)*(Component of upstream mach normal to oblique shock^2))))
  • Density behind shock=Stagnation pressure ahead of shock/(1+((Specific Heat Ratio-1)/2)*(Normal velocity/Old speed of sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-Time))
  • Density behind shock=Stagnation pressure ahead of shock/(1-((Specific Heat Ratio-1)/2)*(Normal velocity/Old speed of sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-Time))
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