Chilvera Bhanu Teja
Institute of Aeronautical Engineering (IARE), Hyderabad
Chilvera Bhanu Teja has created this Calculator and 200+ more calculators!
Sagar S Kulkarni
Dayananda Sagar College of Engineering (DSCE), Bengaluru
Sagar S Kulkarni has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Work done in adiabatic process
Work =(Initial Pressure of System*Initial Volume of System-Final Pressure of System*Final Volume of System)/(Molar Specific Heat Capacity at Constant Pressure/Molar Specific Heat Capacity at Constant Volume-1) GO
Final Temperature in Adiabatic Process (using pressure)
final temp.=initial temp.*(Final Pressure of System/Initial Pressure of System)^(1-1/(Molar Specific Heat Capacity at Constant Pressure/Molar Specific Heat Capacity at Constant Volume)) GO
Entropy change (Isochoric Process) (With given pressures)
Entropy change constant volume=Mass of Gas*Molar Specific Heat Capacity at Constant Volume*ln(Final Pressure of System/Initial Pressure of System) GO
Isothermal work given pressure ratio
Isothermal work given pressure ratio=Final Pressure of System*Volume of gas 1*ln(Initial Pressure of System/Final Pressure of System) GO
Polytropic work
Polytropic work=((Final Pressure of System*Volume of gas 2)-(Initial Pressure of System*Volume of gas 1))/(1-Polytropic index) GO
Ram Efficiency
Ram Efficiency=(Stagnation Pressure-Initial Pressure of System)/(Final Pressure of System-Initial Pressure of System) GO
Isothermal work given volume ratio
Isothermal work given volume ratio=Initial Pressure of System*Volume of gas 1*ln(Volume of gas 2/Volume of gas 1) GO
Isothermal work given temperature
Isothermal work given temperature=[R]*Temperature*ln(Initial Pressure of System/Final Pressure of System) GO
Isobaric work
Isobaric work=Absolute Pressure*(Final Pressure of System-Initial Pressure of System) GO
Work done in isothermal process (using pressure)
Work =[R]*Temperature of Gas*ln(Initial Pressure of System/Final Pressure of System) GO
Heat transferred in isothermal process (using pressure)
Heat=[R]*Temperature of Gas*ln(Initial Pressure of System/Final Pressure of System) GO

11 Other formulas that calculate the same Output

Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
pressure ratio=(1-((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for unsteady waves
pressure ratio=(1+((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio having high mach number with similarity constant
pressure ratio=(1-((Specific Heat Ratio-1)/2)*Hypersonic similarity parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for high Mach number
pressure ratio=(Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for blunt cylinder blast wave
pressure ratio=0.8773*[BoltZ]*(Mach Number^2)*(sqrt(Drag Coefficient))*(Distance from X-axis/Diameter ^(-1)) GO
Pressure ratio for blunt slab blast wave
pressure ratio=0.127*(Mach Number^2)*(Drag Coefficient^(2/3))*((Distance from X-axis/Diameter )^(-2/3)) GO
Exact pressure ratio
pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO
Blunt-nosed flat plate pressure ratio (first approximation)
pressure ratio=0.121*(Mach Number^2)*((Drag Coefficient/(Distance from X-axis/Diameter ))^(2/3)) GO
Pressure ratio when Mach becomes infinite
pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO
Simplified pressure ratio for blunt cylinder blast wave
pressure ratio=0.0681*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ) GO
Pressure ratio of Blunt-nosed cylinder (first approximation):
pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ) GO

Pressure ratio Formula

pressure ratio=Final Pressure of System/Initial Pressure of System
Rp=P<sub>f</sub>/P<sub>i</sub>
More formulas
Speed of Sound GO
Mach Number GO
Mach Angle GO
Stagnation Temperature GO
Heat capacity ratio GO
Internal Energy of a perfect gas at given temperature GO
Enthalpy of ideal gas at given temperature GO
Shaft work in compressible flow machines GO
Shaft work in compressible flow machines neglecting inlet and exit velocities GO
Stagnation Velocity of Sound GO
Stagnation Velocity of Sound if specific heat at constant pressure is known GO
Stagnation Velocity of Sound if stagnation enthalpy is known GO
Mass flow rate of exhaust gases GO
Mass flow rate of exhaust gases if fuel air ratio is known GO

What is pressure ratio?

Pressure ratio is the ratio of final pressure after process to the initial pressure before process. It gives the degree with which gas is compressed.

How to Calculate Pressure ratio?

Pressure ratio calculator uses pressure ratio=Final Pressure of System/Initial Pressure of System to calculate the pressure ratio, The Pressure ratio formula is defined as the ratio of the final pressure after process to the initial pressure before process. pressure ratio and is denoted by Rp symbol.

How to calculate Pressure ratio using this online calculator? To use this online calculator for Pressure ratio, enter Final Pressure of System (Pf) and Initial Pressure of System (Pi) and hit the calculate button. Here is how the Pressure ratio calculation can be explained with given input values -> 10 = 10/1.

FAQ

What is Pressure ratio?
The Pressure ratio formula is defined as the ratio of the final pressure after process to the initial pressure before process and is represented as Rp=Pf/Pi or pressure ratio=Final Pressure of System/Initial Pressure of System. Final Pressure of System is the total final pressure exerted by the molecules inside the system and Initial Pressure of System is the total initial pressure exerted by the molecules inside the system.
How to calculate Pressure ratio?
The Pressure ratio formula is defined as the ratio of the final pressure after process to the initial pressure before process is calculated using pressure ratio=Final Pressure of System/Initial Pressure of System. To calculate Pressure ratio, you need Final Pressure of System (Pf) and Initial Pressure of System (Pi). With our tool, you need to enter the respective value for Final Pressure of System and Initial Pressure of System 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 pressure ratio?
In this formula, pressure ratio uses Final Pressure of System and Initial Pressure of System. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1)
  • pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2)
  • pressure ratio=(Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=(1-((Specific Heat Ratio-1)/2)*Hypersonic similarity parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=0.8773*[BoltZ]*(Mach Number^2)*(sqrt(Drag Coefficient))*(Distance from X-axis/Diameter ^(-1))
  • pressure ratio=0.0681*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter )
  • pressure ratio=0.127*(Mach Number^2)*(Drag Coefficient^(2/3))*((Distance from X-axis/Diameter )^(-2/3))
  • pressure ratio=0.121*(Mach Number^2)*((Drag Coefficient/(Distance from X-axis/Diameter ))^(2/3))
  • pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter )
  • pressure ratio=(1+((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=(1-((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
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