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Pressure Ratio for High Mach Number Formula

GoPressure Ratio having High Mach Number with Similarity Constant Formula

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Pressure Ratio is ratio of final to initial pressure. Check FAQs

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

r_p - Pressure Ratio?M₁ - Mach Number ahead of Shock?M₂ - Mach Number Behind Shock?Y - Specific Heat Ratio?

Pressure Ratio for High Mach Number Example

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Here is how the Pressure Ratio for High Mach Number equation looks like with Values.

Here is how the Pressure Ratio for High Mach Number equation looks like with Units.

Here is how the Pressure Ratio for High Mach Number equation looks like.

350.4666 = {(\frac{1.5}{0.5})}^{2 \cdot \frac{1.6}{1.6 - 1}}

350.4666 = {(\frac{1.5}{0.5})}^{2 \cdot \frac{1.6}{1.6 - 1}}

350.4666 = {(\frac{1.5}{0.5})}^{2 \cdot \frac{1.6}{1.6 - 1}}

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Pressure Ratio for High Mach Number Solution

Follow our step by step solution on how to calculate Pressure Ratio for High Mach Number?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

r p = {(\frac{1.5}{0.5})}^{2 \cdot \frac{1.6}{1.6 - 1}}

Next Step Prepare to Evaluate

∴

r p = {(\frac{1.5}{0.5})}^{2 \cdot \frac{1.6}{1.6 - 1}}

Next Step Evaluate

∴

r p = 350.4666455847

LAST Step Rounding Answer

∴

r p = 350.4666

Pressure Ratio for High Mach Number Formula Elements

Variables

Pressure Ratio

Pressure Ratio is ratio of final to initial pressure.

Symbol: r_p

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Pressure Ratio

Mach Number ahead of Shock

Mach Number ahead of Shock is the Mach number over the body before a shockwave has occurred.

Symbol: M₁

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number ahead of Shock

Mach Number Behind Shock

Mach Number behind shock is the Mach number over the body after a shockwave has occurred.

Symbol: M₂

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number Behind Shock

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

Other Formulas to find Pressure Ratio

Go Pressure Ratio having High Mach Number with Similarity Constant

r p = {(1 - (\frac{Y - 1}{2}) \cdot K)}^{2 \cdot \frac{Y}{Y - 1}}

Other formulas in Hypersonic Flow Parameters category

Go Axial Force Coefficient

μ = \frac{F}{q \cdot A}

Go Coefficient of Drag

C D = \frac{F D}{q \cdot A}

Go Coefficient of Pressure with Similarity Parameters

C p = 2 \cdot θ^{2} \cdot (\frac{Y + 1}{4} + \sqrt{{(\frac{Y + 1}{4})}^{2} + \frac{1}{K^{2}}})

Go Deflection Angle

θ d = \frac{2}{Y - 1} \cdot (\frac{1}{M 1} - \frac{1}{M 2})

How to Evaluate Pressure Ratio for High Mach Number?

Pressure Ratio for High Mach Number evaluator uses Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) to evaluate the Pressure Ratio, Pressure Ratio for High Mach Number formula is defined as a dimensionless quantity that characterizes the compression ratio of a fluid in hypersonic flow, providing a crucial parameter in the analysis of high-speed flow phenomena, particularly in the context of aerospace engineering and aerodynamics. Pressure Ratio is denoted by r_p symbol.

How to evaluate Pressure Ratio for High Mach Number using this online evaluator? To use this online evaluator for Pressure Ratio for High Mach Number, enter Mach Number ahead of Shock (M₁), Mach Number Behind Shock (M₂) & Specific Heat Ratio (Y) and hit the calculate button.

FAQs on Pressure Ratio for High Mach Number

What is the formula to find Pressure Ratio for High Mach Number?

The formula of Pressure Ratio for High Mach Number is expressed as Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)). Here is an example- 350.4666 = (1.5/0.5)^(2*1.6/(1.6-1)).

How to calculate Pressure Ratio for High Mach Number?

With Mach Number ahead of Shock (M₁), Mach Number Behind Shock (M₂) & Specific Heat Ratio (Y) we can find Pressure Ratio for High Mach Number using the formula - Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)).

What are the other ways to Calculate Pressure Ratio?

Here are the different ways to Calculate Pressure Ratio-

Pressure Ratio=(1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

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Pressure Ratio for High Mach Number Formula

​GoPressure Ratio having High Mach Number with Similarity Constant Formula

Pressure Ratio for High Mach Number Example

Pressure Ratio for High Mach Number Solution

Pressure Ratio for High Mach Number Formula Elements

Other Formulas to find Pressure Ratio

Other formulas in Hypersonic Flow Parameters category

How to Evaluate Pressure Ratio for High Mach Number?

FAQs on Pressure Ratio for High Mach Number

Variable Name

GoPressure Ratio having High Mach Number with Similarity Constant Formula