Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ 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

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
Temperature ratio when Mach becomes infinite
Temperature Ratio=(2*Specific Heat Ratio*(Specific Heat Ratio-1))*((Mach Number*sin(Wave angle))^2)/(Specific Heat Ratio+1)^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
Exact pressure ratio
pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) 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

Parallel upstream flow components after shock as Mach tends to infinite Formula

Parallel upstream flow components =Velocity_of the fluid at 1*(1-(2*(sin(Wave angle))^2)/(Specific Heat Ratio-1))
u2=V<sub>1*(1-(2*(sin(β))^2)/(γ-1))
More formulas
Exact pressure ratio GO
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
Perpendicular upstream flow components behind the shock wave GO

What is velocity component?

The two parts of a vector are known as components and describe the influence of that vector in a single direction. If a projectile is launched at an angle to the horizontal, then the initial velocity of the projectile has both a horizontal and a vertical component.

How to Calculate Parallel upstream flow components after shock as Mach tends to infinite?

Parallel upstream flow components after shock as Mach tends to infinite calculator uses Parallel upstream flow components =Velocity_of the fluid at 1*(1-(2*(sin(Wave angle))^2)/(Specific Heat Ratio-1)) to calculate the Parallel upstream flow components , The Parallel upstream flow components after shock as Mach tends to infinite formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite. Parallel upstream flow components and is denoted by u2 symbol.

How to calculate Parallel upstream flow components after shock as Mach tends to infinite using this online calculator? To use this online calculator for Parallel upstream flow components after shock as Mach tends to infinite, enter Velocity_of the fluid at 1 (V1), Wave angle (β) and Specific Heat Ratio (γ) and hit the calculate button. Here is how the Parallel upstream flow components after shock as Mach tends to infinite calculation can be explained with given input values -> 0.134701 = 10*(1-(2*(sin(10))^2)/(1.6-1)).

FAQ

What is Parallel upstream flow components after shock as Mach tends to infinite?
The Parallel upstream flow components after shock as Mach tends to infinite formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite and is represented as u2=V1*(1-(2*(sin(β))^2)/(γ-1)) or Parallel upstream flow components =Velocity_of the fluid at 1*(1-(2*(sin(Wave angle))^2)/(Specific Heat Ratio-1)). Velocity_of the fluid at 1 is defined as the velocity of the flowing liquid at a point 1, Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle and 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.
How to calculate Parallel upstream flow components after shock as Mach tends to infinite?
The Parallel upstream flow components after shock as Mach tends to infinite formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite is calculated using Parallel upstream flow components =Velocity_of the fluid at 1*(1-(2*(sin(Wave angle))^2)/(Specific Heat Ratio-1)). To calculate Parallel upstream flow components after shock as Mach tends to infinite, you need Velocity_of the fluid at 1 (V1), Wave angle (β) and Specific Heat Ratio (γ). With our tool, you need to enter the respective value for Velocity_of the fluid at 1, Wave angle and Specific Heat Ratio and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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