Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Rushi Shah
K J Somaiya College of Engineering (K J Somaiya), Mumbai
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11 Other formulas that you can solve using the same Inputs

Exact Density Ratio
Density ratio=((Specific Heat Ratio+1)*((Mach Number*(sin(Wave angle)))^2))/((Specific Heat Ratio-1)*((Mach Number*(sin(Wave angle)))^2)+2) GO
Ratio of stagnation and static pressure
Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Ratio of Stagnation and Static Density
Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) 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
Pressure ratio when Mach becomes infinite
pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO
Mach number
Mach Number=Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*final temp.)) GO
Ratio of Stagnation and Static Temperature
Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO
Speed of Sound
Speed of Sound=sqrt(Specific Heat Ratio*[R-Dry-Air]*Temperature of Gas) GO
Density ratio when Mach become infinite
Density ratio=(Specific Heat Ratio+1)/(Specific Heat Ratio-1) GO
Mach Angle
Mach Angle=asin(1/Mach Number) 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
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
pressure ratio=Final Pressure of System/Initial Pressure of System GO

Exact pressure ratio Formula

pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1)
Rp=1+(2*γ/(γ+1))*(((M*sin(β))^2)-1)
More formulas
Pressure ratio when Mach becomes infinite GO
Exact Density Ratio GO
Density ratio when Mach become infinite GO
Temperature ratios GO
Temperature ratio when Mach becomes infinite GO
Non-dimensional pressure coefficient GO
Velocity of sound using dynamic pressure and density GO
Dynamic pressure for given specific heat ratio and Mach number GO
Exact relation for pressure coefficient behind an oblique shock wave GO
Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite GO
Wave angle for small deflection angle GO
Coefficient of pressure derived from oblique shock theory GO
Parallel upstream flow components after shock as Mach tends to infinite GO
Perpendicular upstream flow components behind the shock wave GO

What is exact pressure ratio of oblique shock relation?

Pressure ratio or overall pressure ratio, is the ratio of the stagnation pressure as measured at the front and rear of the body moving in hypersonic flow.

How to Calculate Exact pressure ratio?

Exact pressure ratio calculator uses pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) to calculate the pressure ratio, The Exact pressure ratio formula is defined as product of specific heat ratio and the mach number of the flow before impact at an angle. pressure ratio and is denoted by Rp symbol.

How to calculate Exact pressure ratio using this online calculator? To use this online calculator for Exact pressure ratio, enter Specific Heat Ratio (γ), Mach Number (M) and Wave angle (β) and hit the calculate button. Here is how the Exact pressure ratio calculation can be explained with given input values -> -0.193657 = 1+(2*1.6/(1.6+1))*(((1*sin(10))^2)-1).

FAQ

What is Exact pressure ratio?
The Exact pressure ratio formula is defined as product of specific heat ratio and the mach number of the flow before impact at an angle and is represented as Rp=1+(2*γ/(γ+1))*(((M*sin(β))^2)-1) or pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1). The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume, Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound and Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
How to calculate Exact pressure ratio?
The Exact pressure ratio formula is defined as product of specific heat ratio and the mach number of the flow before impact at an angle is calculated using pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1). To calculate Exact pressure ratio, you need Specific Heat Ratio (γ), Mach Number (M) and Wave angle (β). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number and Wave angle 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 Specific Heat Ratio, Mach Number and Wave angle. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • 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=Final Pressure of System/Initial Pressure of System
  • 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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