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Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Formula

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Stagnation Pressure Behind Normal Shock is the stagnation or total or pitot pressure after passing through shock. Check FAQs

p 02 = P 1 \cdot (\frac{1 - γ + 2 \cdot γ \cdot {M 1}^{2}}{γ + 1}) \cdot {(\frac{{(γ + 1)}^{2} \cdot {M 1}^{2}}{4 \cdot γ \cdot {M 1}^{2} - 2 \cdot (γ - 1)})}^{\frac{γ}{γ - 1}}

p₀₂ - Stagnation Pressure Behind Normal Shock?P₁ - Static Pressure Ahead of Normal Shock?γ - Specific Heat Ratio?M₁ - Mach Number Ahead of Normal Shock?

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Example

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Here is how the Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula equation looks like with Values.

Here is how the Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula equation looks like with Units.

Here is how the Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula equation looks like.

220.6775 = 65.374 \cdot (\frac{1 - 1.4 + 2 \cdot 1.4 \cdot {1.49}^{2}}{1.4 + 1}) \cdot {(\frac{{(1.4 + 1)}^{2} \cdot {1.49}^{2}}{4 \cdot 1.4 \cdot {1.49}^{2} - 2 \cdot (1.4 - 1)})}^{\frac{1.4}{1.4 - 1}}

220.6775Pa = 65.374Pa \cdot (\frac{1 - 1.4 + 2 \cdot 1.4 \cdot {1.49}^{2}}{1.4 + 1}) \cdot {(\frac{{(1.4 + 1)}^{2} \cdot {1.49}^{2}}{4 \cdot 1.4 \cdot {1.49}^{2} - 2 \cdot (1.4 - 1)})}^{\frac{1.4}{1.4 - 1}}

220.6775 = 65.374 \cdot (\frac{1 - 1.4 + 2 \cdot 1.4 \cdot {1.49}^{2}}{1.4 + 1}) \cdot {(\frac{{(1.4 + 1)}^{2} \cdot {1.49}^{2}}{4 \cdot 1.4 \cdot {1.49}^{2} - 2 \cdot (1.4 - 1)})}^{\frac{1.4}{1.4 - 1}}

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Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Solution

Follow our step by step solution on how to calculate Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

FIRST Step Consider the formula

p 02 = P 1 \cdot (\frac{1 - γ + 2 \cdot γ \cdot {M 1}^{2}}{γ + 1}) \cdot {(\frac{{(γ + 1)}^{2} \cdot {M 1}^{2}}{4 \cdot γ \cdot {M 1}^{2} - 2 \cdot (γ - 1)})}^{\frac{γ}{γ - 1}}

Next Step Substitute values of Variables

∴

p 02 = 65.374Pa \cdot (\frac{1 - 1.4 + 2 \cdot 1.4 \cdot {1.49}^{2}}{1.4 + 1}) \cdot {(\frac{{(1.4 + 1)}^{2} \cdot {1.49}^{2}}{4 \cdot 1.4 \cdot {1.49}^{2} - 2 \cdot (1.4 - 1)})}^{\frac{1.4}{1.4 - 1}}

Next Step Prepare to Evaluate

∴

p 02 = 65.374 \cdot (\frac{1 - 1.4 + 2 \cdot 1.4 \cdot {1.49}^{2}}{1.4 + 1}) \cdot {(\frac{{(1.4 + 1)}^{2} \cdot {1.49}^{2}}{4 \cdot 1.4 \cdot {1.49}^{2} - 2 \cdot (1.4 - 1)})}^{\frac{1.4}{1.4 - 1}}

Next Step Evaluate

∴

p 02 = 220.677542531544Pa

LAST Step Rounding Answer

∴

p 02 = 220.6775Pa

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Formula Elements

Variables

Stagnation Pressure Behind Normal Shock

Stagnation Pressure Behind Normal Shock is the stagnation or total or pitot pressure after passing through shock.

Symbol: p₀₂

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Stagnation 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 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 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}

How to Evaluate Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula evaluator uses Stagnation Pressure Behind Normal Shock = Static Pressure Ahead of Normal Shock*((1-Specific Heat Ratio+2*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2)/(Specific Heat Ratio+1))*(((Specific Heat Ratio+1)^2*Mach Number Ahead of Normal Shock^2)/(4*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-2*(Specific Heat Ratio-1)))^((Specific Heat Ratio)/(Specific Heat Ratio-1)) to evaluate the Stagnation Pressure Behind Normal Shock, Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula is a representation of the pressure changes occurring in a compressible flow when a normal shock wave is present, highlighting the relationship between upstream conditions and downstream stagnation pressure. Stagnation Pressure Behind Normal Shock is denoted by p₀₂ symbol.

How to evaluate Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula using this online evaluator? To use this online evaluator for Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula, 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 Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula

What is the formula to find Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

The formula of Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula is expressed as Stagnation Pressure Behind Normal Shock = Static Pressure Ahead of Normal Shock*((1-Specific Heat Ratio+2*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2)/(Specific Heat Ratio+1))*(((Specific Heat Ratio+1)^2*Mach Number Ahead of Normal Shock^2)/(4*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-2*(Specific Heat Ratio-1)))^((Specific Heat Ratio)/(Specific Heat Ratio-1)). Here is an example- 220.6775 = 65.374*((1-1.4+2*1.4*1.49^2)/(1.4+1))*(((1.4+1)^2*1.49^2)/(4*1.4*1.49^2-2*(1.4-1)))^((1.4)/(1.4-1)).

How to calculate Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

With Static Pressure Ahead of Normal Shock (P₁), Specific Heat Ratio (γ) & Mach Number Ahead of Normal Shock (M₁) we can find Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula using the formula - Stagnation Pressure Behind Normal Shock = Static Pressure Ahead of Normal Shock*((1-Specific Heat Ratio+2*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2)/(Specific Heat Ratio+1))*(((Specific Heat Ratio+1)^2*Mach Number Ahead of Normal Shock^2)/(4*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-2*(Specific Heat Ratio-1)))^((Specific Heat Ratio)/(Specific Heat Ratio-1)).

Can the Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula be negative?

No, the Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula, measured in Pressure cannot be negative.

Which unit is used to measure Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula 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 Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula can be measured.

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Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Formula

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Example

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Solution

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula Formula Elements

Other formulas in Downstream Shock Waves category

How to Evaluate Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula?

FAQs on Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula

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