Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Calculator

✖Velocity of the fluid at 1 is defined as the velocity of the flowing liquid at a point 1.ⓘ Velocity of the fluid at 1 [V₁]			+10% -10%
✖Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.ⓘ Wave Angle [β]			+10% -10%
✖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.ⓘ Specific Heat Ratio [Y]			+10% -10%

✖Parallel upstream flow components of the flow velocity behind the shock wave parallel to the upstream flow.ⓘ Parallel Upstream Flow Components after Shock as Mach Tends to Infinite [u2]

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Formula

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Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

Formula

`"u2" = "V"_{"1"}*(1-(2*(sin("β"))^2)/("Y"-1))`

Example

`"19.24914m/s"="26.2m/s"*(1-(2*(sin("0.286rad"))^2)/("1.6"-1))`

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Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Solution

STEP 0: Pre-Calculation Summary

Formula Used

Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))
u2 = V₁*(1-(2*(sin(β))^2)/(Y-1))
This formula uses 1 Functions, 4 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Parallel upstream flow components - (Measured in Meter per Second) - Parallel upstream flow components of the flow velocity behind the shock wave parallel to the upstream flow.
Velocity of the fluid at 1 - (Measured in Meter per Second) - Velocity of the fluid at 1 is defined as the velocity of the flowing liquid at a point 1.
Wave Angle - (Measured in Radian) - Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
Specific Heat Ratio - 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.

STEP 1: Convert Input(s) to Base Unit

Velocity of the fluid at 1: 26.2 Meter per Second --> 26.2 Meter per Second No Conversion Required
Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

u2 = V₁*(1-(2*(sin(β))^2)/(Y-1)) --> 26.2*(1-(2*(sin(0.286))^2)/(1.6-1))

Evaluating ... ...

u2 = 19.2491412219209

STEP 3: Convert Result to Output's Unit

19.2491412219209 Meter per Second --> No Conversion Required

FINAL ANSWER

19.2491412219209 ≈ 19.24914 Meter per Second <-- Parallel upstream flow components

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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PSG College of Technology (PSGCT), Coimbatore

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< 15 Oblique Shock Relation Calculators

Exact Density Ratio

Go Density Ratio = ((Specific Heat Ratio+1)*(Mach Number*(sin(Wave Angle)))^2)/((Specific Heat Ratio-1)*(Mach Number*(sin(Wave Angle)))^2+2)

Temperature Ratio when Mach Becomes Infinite

Go Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2

Exact Pressure Ratio

Go Pressure Ratio = 1+2*Specific Heat Ratio/(Specific Heat Ratio+1)*((Mach Number*sin(Wave Angle))^2-1)

Pressure Ratio when Mach becomes Infinite

Go Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

Go Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))

Perpendicular Upstream Flow Components behind Shock Wave

Go Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)

Pressure Coefficient behind Oblique Shock Wave

Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)

Wave Angle for Small Deflection Angle

Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180

Velocity of Sound using Dynamic Pressure and Density

Go Speed of Sound = sqrt((Specific Heat Ratio*Pressure)/Density)

Dynamic Pressure for given Specific Heat Ratio and Mach Number

Go Dynamic Pressure = Specific Heat Ratio Dynamic*Static Pressure*(Mach Number^2)/2

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number

Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2

Non-Dimensional Pressure Coefficient

Go Pressure Coefficient = Change in static pressure/Dynamic Pressure

Density Ratio when Mach Becomes Infinite

Go Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)

Temperature Ratios

Go Temperature Ratio = Pressure Ratio/Density Ratio

Coefficient of Pressure Derived from Oblique Shock Theory

Go Pressure Coefficient = 2*(sin(Wave Angle))^2

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 = V₁*(1-(2*(sin(β))^2)/(Y-1))

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 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) & Specific Heat Ratio (Y) 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 -> 19.23808 = 26.2*(1-(2*(sin(0.286))^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)/(Y-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 & 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) & Specific Heat Ratio (Y). With our tool, you need to enter the respective value for Velocity of the fluid at 1, Wave Angle & 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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