Density Ratio when Mach Becomes Infinite Calculator

✖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]

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✖Density Ratio higher is also one of the definitions of hypersonic flow. Density ratio across normal shock would reach 6 for calorically perfect gas (air or diatomic gas) at very high Mach numbers.ⓘ Density Ratio when Mach Becomes Infinite [ρ_ratio]

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Density Ratio when Mach Becomes Infinite Solution

STEP 0: Pre-Calculation Summary

Formula Used

Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)
ρ_ratio = (Y+1)/(Y-1)
This formula uses 2 Variables

Variables Used

Density Ratio - Density Ratio higher is also one of the definitions of hypersonic flow. Density ratio across normal shock would reach 6 for calorically perfect gas (air or diatomic gas) at very high Mach numbers.
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

Specific Heat Ratio: 1.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

ρ_ratio = (Y+1)/(Y-1) --> (1.6+1)/(1.6-1)

Evaluating ... ...

ρ_ratio = 4.33333333333333

STEP 3: Convert Result to Output's Unit

4.33333333333333 --> No Conversion Required

FINAL ANSWER

4.33333333333333 ≈ 4.333333 <-- Density Ratio

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

Verified by Rushi Shah

K J Somaiya College of Engineering (K J Somaiya), Mumbai

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< Oblique Shock Relation Calculators

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

LaTeX Go Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))

Perpendicular Upstream Flow Components behind Shock Wave

LaTeX Go Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)

Wave Angle for Small Deflection Angle

LaTeX Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180

Coefficient of Pressure Derived from Oblique Shock Theory

LaTeX Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Density Ratio when Mach Becomes Infinite Formula

LaTeX Go

Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)
ρ_ratio = (Y+1)/(Y-1)

What is density ratio if Mach is infinite?

Higher density ratio is also one of the definitions of hypersonic flow. Density ratio across normal shock would reach 6 for calorically perfect gas (air or diatomic gas) at very high Mach numbers

How to Calculate Density Ratio when Mach Becomes Infinite?

Density Ratio when Mach Becomes Infinite calculator uses Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1) to calculate the Density Ratio, Density Ratio when Mach Becomes Infinite formula is defined as a measure of the ratio of the density of a fluid in a normal shock wave to the density of the same fluid in an oblique shock wave, which occurs when the Mach number becomes infinite in a compressible flow. Density Ratio is denoted by ρ_ratio symbol.

How to calculate Density Ratio when Mach Becomes Infinite using this online calculator? To use this online calculator for Density Ratio when Mach Becomes Infinite, enter Specific Heat Ratio (Y) and hit the calculate button. Here is how the Density Ratio when Mach Becomes Infinite calculation can be explained with given input values -> 4.333333 = (1.6+1)/(1.6-1).

FAQ

What is Density Ratio when Mach Becomes Infinite?

Density Ratio when Mach Becomes Infinite formula is defined as a measure of the ratio of the density of a fluid in a normal shock wave to the density of the same fluid in an oblique shock wave, which occurs when the Mach number becomes infinite in a compressible flow and is represented as ρ_ratio = (Y+1)/(Y-1) or Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1). 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 Density Ratio when Mach Becomes Infinite?

Density Ratio when Mach Becomes Infinite formula is defined as a measure of the ratio of the density of a fluid in a normal shock wave to the density of the same fluid in an oblique shock wave, which occurs when the Mach number becomes infinite in a compressible flow is calculated using Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1). To calculate Density Ratio when Mach Becomes Infinite, you need Specific Heat Ratio (Y). With our tool, you need to enter the respective value for 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 Density Ratio?

In this formula, Density Ratio uses Specific Heat Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

Density Ratio = ((Specific Heat Ratio+1)*(Mach Number*(sin(Wave Angle)))^2)/((Specific Heat Ratio-1)*(Mach Number*(sin(Wave Angle)))^2+2)

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