Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has created this Calculator and 100+ more calculators!
Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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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

1 Other formulas that calculate the same Output

Density ratio across the oblique shock
Density ratio across 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 ratio across a normal shock Formula

Density ratio across 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
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

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 ratio across a normal shock?

Density ratio across a normal shock calculator uses Density ratio across 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 ratio across shock, Density ratio across a normal shock formula is defined as the ratio of downstream to upstream density across the normal shock. It is a function of specific heat ratio and upstream Mach number. Density ratio across shock and is denoted by ρ21 symbol.

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

FAQ

What is Density ratio across a normal shock?
Density ratio across a normal shock formula is defined as the ratio of downstream to upstream density across the normal shock. It is a function of specific heat ratio and upstream Mach number and is represented as ρ21=(κ+1)*(M1^2)/(2+((κ-1)*(M1^2))) or Density ratio across shock=(Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2))). 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 ratio across a normal shock?
Density ratio across a normal shock formula is defined as the ratio of downstream to upstream density across the normal shock. It is a function of specific heat ratio and upstream Mach number is calculated using Density ratio across 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 ratio across a normal shock, you need Specific heat ratio (κ) and Mach Number ahead of shock (M1). With our tool, you need to enter the respective value for 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 ratio across shock?
In this formula, Density ratio across shock uses Specific heat ratio and Mach Number ahead of shock. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Density ratio across 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)))
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