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
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Mach Number behind the shock
Mach Number behind shock=((2+(Specific heat ratio*(Mach Number ahead of shock^2))-(Mach Number ahead of shock^2))/((2*Specific heat ratio*(Mach Number ahead of shock^2))-Specific heat ratio+1))^(1/2) GO
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
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 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
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)))) GO

Density behind oblique shock for given upstream density & normal upstream Mach no. Formula

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))))
ρ <sub>2</sub>=ρ <sub>1</sub>*((κ+1)*(M<sub>n1</sub>^2)/(2+((κ-1)*(M<sub>n1</sub>^2))))
More formulas
Component of Upstream Mach normal to oblique shock GO
Component of Downstream Mach normal to oblique shock GO
Flow deflection angle GO
Density ratio across the oblique shock GO
Pressure ratio across the oblique shock GO
Temperature ratio across the oblique shock GO
Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no. GO
Pressure behind oblique shock for given upstream pressure & normal upstream Mach no GO
Temperature behind oblique shock for given upstream temperature & normal upstream Mach no. GO
Pressure ratio across the expansion fan GO
Temperature ratio across the expansion fan GO
Pressure behind expansion fan GO
Temperature behind expansion fan GO
Forward Mach angle of expansion fan GO
Rearward Mach angle of the expansion fan GO
Prandtl Meyer function GO
Flow deflection angle in terms of Prandtl Meyer function GO
Prandtl Meyer function at upstream Mach no. GO

Which parameters govern the changes of flow properties across oblique shock?

Oblique shock wave properties in a calorically perfect gas depend only on the normal component of upstream Mach no and which in turn is a function of upstream Mach no. and wave angle. In contrast, the changes in flow properties across normal shock depend on upstream Mach no only.

How to Calculate Density behind oblique shock for given upstream density & normal upstream Mach no.?

Density behind oblique shock for given upstream density & normal upstream Mach no. calculator uses 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)))) to calculate the Density behind shock, The Density behind oblique shock for given upstream density & normal upstream Mach no. formula is obtained by multiplying density ratio across the oblique shock to the density ahead of the oblique shock. Density behind shock and is denoted by ρ 2 symbol.

How to calculate Density behind oblique shock for given upstream density & normal upstream Mach no. using this online calculator? To use this online calculator for Density behind oblique shock for given upstream density & normal upstream Mach no., enter density ahead of shock 1), Specific heat ratio (κ) and Component of upstream mach normal to oblique shock (Mn1) and hit the calculate button. Here is how the Density behind oblique shock for given upstream density & normal upstream Mach no. calculation can be explained with given input values -> 2.680187 = 1*((1.392758+1)*(2^2)/(2+((1.392758-1)*(2^2)))).

FAQ

What is Density behind oblique shock for given upstream density & normal upstream Mach no.?
The Density behind oblique shock for given upstream density & normal upstream Mach no. formula is obtained by multiplying density ratio across the oblique shock to the density ahead of the oblique shock and is represented as ρ 21*((κ+1)*(Mn1^2)/(2+((κ-1)*(Mn1^2)))) or 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 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 Component of upstream mach normal to oblique shock is that component of upstream Mach number which is normal to oblique shockwave.
How to calculate Density behind oblique shock for given upstream density & normal upstream Mach no.?
The Density behind oblique shock for given upstream density & normal upstream Mach no. formula is obtained by multiplying density ratio across the oblique shock to the density ahead of the oblique shock is calculated using 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)))). To calculate Density behind oblique shock for given upstream density & normal upstream Mach no., you need density ahead of shock 1), Specific heat ratio (κ) and Component of upstream mach normal to oblique shock (Mn1). With our tool, you need to enter the respective value for density ahead of shock, Specific heat ratio and Component of upstream mach normal to oblique 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 Component of upstream mach normal to oblique 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)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of 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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