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Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Formula

GoStatic Pressure behind Normal Shock using Normal Shock Momentum Equation Formula

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Static Pressure Behind Normal Shock denotes the pressure of a fluid after passing through a normal shock wave. Check FAQs

P 2 = P 1 \cdot (1 + (\frac{2 \cdot γ}{γ + 1}) \cdot ({M 1}^{2} - 1))

P₂ - Static pressure Behind Normal shock?P₁ - Static Pressure Ahead of Normal Shock?γ - Specific Heat Ratio?M₁ - Mach Number Ahead of Normal Shock?

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Example

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Here is how the Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number equation looks like with Values.

Here is how the Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number equation looks like with Units.

Here is how the Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number equation looks like.

158.4306 = 65.374 \cdot (1 + (\frac{2 \cdot 1.4}{1.4 + 1}) \cdot ({1.49}^{2} - 1))

158.4306Pa = 65.374Pa \cdot (1 + (\frac{2 \cdot 1.4}{1.4 + 1}) \cdot ({1.49}^{2} - 1))

158.4306 = 65.374 \cdot (1 + (\frac{2 \cdot 1.4}{1.4 + 1}) \cdot ({1.49}^{2} - 1))

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Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Solution

Follow our step by step solution on how to calculate Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

FIRST Step Consider the formula

P 2 = P 1 \cdot (1 + (\frac{2 \cdot γ}{γ + 1}) \cdot ({M 1}^{2} - 1))

Next Step Substitute values of Variables

∴

P 2 = 65.374Pa \cdot (1 + (\frac{2 \cdot 1.4}{1.4 + 1}) \cdot ({1.49}^{2} - 1))

Next Step Prepare to Evaluate

∴

P 2 = 65.374 \cdot (1 + (\frac{2 \cdot 1.4}{1.4 + 1}) \cdot ({1.49}^{2} - 1))

Next Step Evaluate

∴

P 2 = 158.4306203Pa

LAST Step Rounding Answer

∴

P 2 = 158.4306Pa

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Formula Elements

Variables

Static pressure Behind Normal shock

Static Pressure Behind Normal Shock denotes the pressure of a fluid after passing through a normal shock wave.

Symbol: P₂

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Static pressure Behind Normal shock

Static Pressure Ahead of Normal Shock

Static Pressure Ahead of Normal Shock is the pressure in the upstream direction of shock.

Symbol: P₁

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Static Pressure Ahead of Normal Shock

Specific Heat Ratio

The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.

Symbol: γ

Measurement: NAUnit: Unitless

Note: Value should be between 1 to 2.

Formulas to find Specific Heat Ratio

Mach Number Ahead of Normal Shock

Mach Number Ahead of Normal Shock represents the velocity of a fluid or airflow relative to the speed of sound before encountering a normal shock wave.

Symbol: M₁

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number Ahead of Normal Shock

Other Formulas to find Static pressure Behind Normal shock

Go Static Pressure behind Normal Shock using Normal Shock Momentum Equation

P 2 = P 1 + ρ 1 \cdot {V 1}^{2} - ρ 2 \cdot {V 2}^{2}

Other formulas in Downstream Shock Waves category

Go Characteristic Mach Number behind Shock

M2 cr = \frac{1}{M1 cr}

Go Mach Number behind Shock

M 2 = {(\frac{2 + γ \cdot {M 1}^{2} - {M 1}^{2}}{2 \cdot γ \cdot {M 1}^{2} - γ + 1})}^{\frac{1}{2}}

Go Velocity behind Normal Shock

V 2 = \frac{V 1}{\frac{γ + 1}{(γ - 1) + \frac{2}{M^{2}}}}

Go Density behind Normal Shock using Normal Shock Momentum Equation

ρ 2 = \frac{P 1 + ρ 1 \cdot {V 1}^{2} - P 2}{{V 2}^{2}}

How to Evaluate Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number evaluator uses Static pressure Behind Normal shock = Static Pressure Ahead of Normal Shock*(1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1)) to evaluate the Static pressure Behind Normal shock, Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number formula is defined as a relationship that describes how pressure changes across a normal shock wave in compressible flow, influenced by upstream pressure and the Mach number of the flow. Static pressure Behind Normal shock is denoted by P₂ symbol.

How to evaluate Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number using this online evaluator? To use this online evaluator for Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number, enter Static Pressure Ahead of Normal Shock (P₁), Specific Heat Ratio (γ) & Mach Number Ahead of Normal Shock (M₁) and hit the calculate button.

FAQs on Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number

What is the formula to find Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

The formula of Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number is expressed as Static pressure Behind Normal shock = Static Pressure Ahead of Normal Shock*(1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1)). Here is an example- 65.52662 = 65.374*(1+((2*1.4)/(1.4+1))*(1.49^2-1)).

How to calculate Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

With Static Pressure Ahead of Normal Shock (P₁), Specific Heat Ratio (γ) & Mach Number Ahead of Normal Shock (M₁) we can find Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number using the formula - Static pressure Behind Normal shock = Static Pressure Ahead of Normal Shock*(1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1)).

What are the other ways to Calculate Static pressure Behind Normal shock?

Here are the different ways to Calculate Static pressure Behind Normal shock-

Static pressure Behind Normal shock=Static Pressure Ahead of Normal Shock+Density Ahead of Normal Shock*Velocity Upstream of Shock^2-Density Behind Normal Shock*Velocity Downstream of Shock^2

Can the Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number be negative?

No, the Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number, measured in Pressure cannot be negative.

Which unit is used to measure Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number is usually measured using the Pascal[Pa] for Pressure. Kilopascal[Pa], Bar[Pa], Pound Per Square Inch[Pa] are the few other units in which Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number can be measured.

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Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Formula

​GoStatic Pressure behind Normal Shock using Normal Shock Momentum Equation Formula

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Example

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Solution

Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number Formula Elements

Other Formulas to find Static pressure Behind Normal shock

Other formulas in Downstream Shock Waves category

How to Evaluate Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number?

FAQs on Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number

Variable Name

GoStatic Pressure behind Normal Shock using Normal Shock Momentum Equation Formula