Pressure Ratio for High Mach Number Calculator

✖Mach Number ahead of Shock is the Mach number over the body before a shockwave has occurred.ⓘ Mach Number ahead of Shock [M₁]			+10% -10%
✖Mach Number behind shock is the Mach number over the body after a shockwave has occurred.ⓘ Mach Number Behind Shock [M₂]			+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%

✖Pressure Ratio is ratio of final to initial pressure.ⓘ Pressure Ratio for High Mach Number [r_p]

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Pressure Ratio for High Mach Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
r_p = (M₁/M₂)^(2*Y/(Y-1))
This formula uses 4 Variables

Variables Used

Pressure Ratio - Pressure Ratio is ratio of final to initial pressure.
Mach Number ahead of Shock - Mach Number ahead of Shock is the Mach number over the body before a shockwave has occurred.
Mach Number Behind Shock - Mach Number behind shock is the Mach number over the body after a shockwave has occurred.
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

Mach Number ahead of Shock: 1.5 --> No Conversion Required
Mach Number Behind Shock: 0.5 --> No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

r_p = (M₁/M₂)^(2*Y/(Y-1)) --> (1.5/0.5)^(2*1.6/(1.6-1))

Evaluating ... ...

r_p = 350.4666455847

STEP 3: Convert Result to Output's Unit

350.4666455847 --> No Conversion Required

FINAL ANSWER

350.4666455847 ≈ 350.4666 <-- Pressure Ratio

(Calculation completed in 00.017 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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< Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

LaTeX Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))

Deflection Angle

LaTeX Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of Shock-1/Mach Number Behind Shock)

Coefficient of Drag

LaTeX Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area For Flow)

Axial Force Coefficient

LaTeX Go Coefficient of Force = Force/(Dynamic Pressure*Area For Flow)

Pressure Ratio for High Mach Number Formula

LaTeX Go

Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
r_p = (M₁/M₂)^(2*Y/(Y-1))

What is pressure ratio for high mach numbers?

Pressure ratio equation changes when the Mach number gets high as many variables get removed as it's too small to cause a change.

How to Calculate Pressure Ratio for High Mach Number?

Pressure Ratio for High Mach Number calculator uses Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) to calculate 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 calculate Pressure Ratio for High Mach Number using this online calculator? To use this online calculator 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. Here is how the Pressure Ratio for High Mach Number calculation can be explained with given input values -> 350.4666 = (1.5/0.5)^(2*1.6/(1.6-1)).

FAQ

What is Pressure Ratio for High Mach Number?

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 and is represented as r_p = (M₁/M₂)^(2*Y/(Y-1)) or Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)). Mach Number ahead of Shock is the Mach number over the body before a shockwave has occurred, Mach Number behind shock is the Mach number over the body after a shockwave has occurred & 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 Pressure Ratio for High Mach Number?

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 is calculated using Pressure Ratio = (Mach Number ahead of Shock/Mach Number Behind Shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)). To calculate Pressure Ratio for High Mach Number, you need Mach Number ahead of Shock (M₁), Mach Number Behind Shock (M₂) & Specific Heat Ratio (Y). With our tool, you need to enter the respective value for Mach Number ahead of Shock, Mach Number Behind Shock & Specific Heat Ratio and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Pressure Ratio?

In this formula, Pressure Ratio uses Mach Number ahead of Shock, Mach Number Behind Shock & Specific Heat Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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