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]

⎘ Copy

👎

Formula

✖

Pressure Ratio for High Mach Number

Formula

`"r"_{"p"} = ("M"_{"1"}/"M"_{"2"})^(2*"Y"/("Y"-1))`

Example

`"350.4666"=("1.5"/"0.5")^(2*"1.6"/("1.6"-1))`

Calculator

LaTeX

Reset

👍

Download Hypersonic Flow Formula PDF PDF Image

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 00.004 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Hypersonic Flow Parameters » Pressure Ratio for High Mach Number

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

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))

Pressure Ratio having High Mach Number with Similarity Constant

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

Mach Number with Fluids

Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))

Pressure Ratio for High Mach Number

Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

Moment Coefficient

Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)

Deflection Angle

Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)

Normal Force Coefficient

Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle

Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))

Dynamic Pressure given Coefficient of Lift

Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)

Coefficient of Drag

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

Dynamic Pressure

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

Lift Coefficient

Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)

Axial Force Coefficient

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

Drag Force

Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow

Lift Force

Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow

Mach Ratio at High Mach Number

Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)

Hypersonic Similarity Parameter

Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle

Shear-Stress Distribution

Go Shear Stress = Viscosity Coefficient*Velocity Gradient

Fourier's Law of Heat Conduction

Go Heat Flux = Thermal Conductivity*Temperature Gradient

Newtonian Sine Squared Law for Pressure Coefficient

Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Pressure Ratio for High Mach Number Formula

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, The Pressure ratio for high Mach number formula is defined as the ratio of Mach number before and after the shock raise to the power of specific heat ratio. 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?

The Pressure ratio for high Mach number formula is defined as the ratio of Mach number before and after the shock raise to the power of specific heat ratio 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?

The Pressure ratio for high Mach number formula is defined as the ratio of Mach number before and after the shock raise to the power of specific heat ratio 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))

Home

FREE PDFs

🔍 Search