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

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Parallel upstream flow components of the flow velocity behind the shock wave parallel to the upstream flow. Check FAQs

u2 = V 1 \cdot (1 - \frac{2 \cdot {(\sin (β))}^{2}}{Y - 1})

u2 - Parallel upstream flow components?V₁ - Velocity of the fluid at 1?β - Wave Angle?Y - Specific Heat Ratio?

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

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Here is how the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite equation looks like with Values.

Here is how the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite equation looks like with Units.

Here is how the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite equation looks like.

19.2491 = 26.2 \cdot (1 - \frac{2 \cdot {(\sin (0.286))}^{2}}{1.6 - 1})

19.2491m/s = 26.2m/s \cdot (1 - \frac{2 \cdot {(\sin (0.286rad))}^{2}}{1.6 - 1})

19.2491 = 26.2 \cdot (1 - \frac{2 \cdot {(\sin (0.286))}^{2}}{1.6 - 1})

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

Follow our step by step solution on how to calculate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

FIRST Step Consider the formula

u2 = V 1 \cdot (1 - \frac{2 \cdot {(\sin (β))}^{2}}{Y - 1})

Next Step Substitute values of Variables

∴

u2 = 26.2m/s \cdot (1 - \frac{2 \cdot {(\sin (0.286rad))}^{2}}{1.6 - 1})

Next Step Prepare to Evaluate

∴

u2 = 26.2 \cdot (1 - \frac{2 \cdot {(\sin (0.286))}^{2}}{1.6 - 1})

Next Step Evaluate

∴

u2 = 19.2491412219209m/s

LAST Step Rounding Answer

∴

u2 = 19.2491m/s

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Formula Elements

Variables

Functions

Parallel upstream flow components

Parallel upstream flow components of the flow velocity behind the shock wave parallel to the upstream flow.

Symbol: u2

Measurement: SpeedUnit: m/s

Note: Value can be positive or negative.

Formulas to find Parallel upstream flow components

Velocity of the fluid at 1

Velocity of the fluid at 1 is defined as the velocity of the flowing liquid at a point 1.

Symbol: V₁

Measurement: SpeedUnit: m/s

Note: Value can be positive or negative.

Formulas to find Velocity of the fluid at 1

Wave Angle

Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

Symbol: β

Measurement: AngleUnit: rad

Note: Value should be greater than 0.

Formulas to find Wave 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.

Symbol: Y

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Specific Heat Ratio

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.

Syntax: sin(Angle)

Other formulas in Oblique Shock Relation category

Go Wave Angle for Small Deflection Angle

β = \frac{Y + 1}{2} \cdot (θ d \cdot \frac{180}{π}) \cdot \frac{π}{180}

Go Coefficient of Pressure Derived from Oblique Shock Theory

C p = 2 \cdot {(\sin (β))}^{2}

Go Perpendicular Upstream Flow Components behind Shock Wave

v2 = \frac{V 1 \cdot (\sin (2 \cdot β))}{Y - 1}

Go Exact Pressure Ratio

r p = 1 + 2 \cdot \frac{Y}{Y + 1} \cdot ({(M \cdot \sin (β))}^{2} - 1)

How to Evaluate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite evaluator uses Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)) to evaluate 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 evaluate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite using this online evaluator? To use this online evaluator 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.

FAQs on Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

What is the formula to find Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

The formula of Parallel Upstream Flow Components after Shock as Mach Tends to Infinite is expressed as Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)). Here is an example- 19.23808 = 26.2*(1-(2*(sin(0.286))^2)/(1.6-1)).

How to calculate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

With Velocity of the fluid at 1 (V₁), Wave Angle (β) & Specific Heat Ratio (Y) we can find Parallel Upstream Flow Components after Shock as Mach Tends to Infinite using the formula - Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)). This formula also uses Sine function(s).

Can the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite be negative?

Yes, the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite, measured in Speed can be negative.

Which unit is used to measure Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite is usually measured using the Meter per Second[m/s] for Speed. Meter per Minute[m/s], Meter per Hour[m/s], Kilometer per Hour[m/s] are the few other units in which Parallel Upstream Flow Components after Shock as Mach Tends to Infinite can be measured.

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

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

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

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Formula Elements

Other formulas in Oblique Shock Relation category

How to Evaluate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

FAQs on Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

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