Mach wave behind the shock with mach infinity Calculator

Category	Engineering ↺
Engineering	Mechanical ↺
Mechanical	Fluid Mechanics ↺
Fluid-Mechanics	Hypersonic Flow ↺
Hypersonic-Flow	Hypersonic Inviscid Flowfields: Exact Methods ↺

✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of soundⓘ Mach Number [M]			+10% -10%
✖local shock velocity, is the shock velocity after the shock waveⓘ local shock velocity [W]			+10% -10%
✖The speed of sound is defined as the dynamic propagation of sound waves.ⓘ Speed of Sound [𝒶]			+10% -10%

✖Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred ⓘ Mach wave behind the shock with mach infinity [M₁]

⎘ Copy

👎 Report Issue!

👍 Share Now!

You are here:

Home »
Engineering »
Mechanical »
Fluid Mechanics »
Hypersonic Flow »
Hypersonic Inviscid Flowfields: Exact Methods »
Mach wave behind the shock with mach infinity

Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 200+ more calculators!

Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Exact Density Ratio

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

Temperature ratio when Mach becomes infinite

Temperature Ratio=(2*Specific Heat Ratio*(Specific Heat Ratio-1))*((Mach Number*sin(Wave angle))^2)/(Specific Heat Ratio+1)^2 GO

Ratio of stagnation and static pressure

Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO

Ratio of Stagnation and Static Density

Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) GO

Relation between Characteristic Mach number and Mach number

Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 GO

Exact pressure ratio

pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO

Pressure ratio when Mach becomes infinite

pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO

Ratio of Stagnation and Static Temperature

Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO

Dynamic pressure for given specific heat ratio and Mach number

Dynamic Pressure=Specific heat ratio*Static pressure*(Mach Number^2)/2 GO

Mach Number

Mach Number=Speed of a body/Speed of Sound GO

Mach Angle

Mach Angle=asin(1/Mach Number) GO

Mach wave behind the shock with mach infinity Formula

Mach Number ahead of shock=Mach Number-(local shock velocity/Speed of Sound)
M<sub>1</sub>=M-(W/𝒶)

More formulas

Grid point calculation for shock waves GO

Mach wave behind the shock GO

Local shock velocity equation GO

Pressure ratio for unsteady waves GO

Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves GO

Temperature ratio for unsteady compression waves GO

Temperature ratio for unsteady expansion wave GO

New pressure after the shock formation for compression wave GO

New pressure after the shock formation, subtracted to velocity for expansion wave GO

Density before shock formation for compression wave GO

Density before the shock formation for expansion wave GO

Ratio of new and old temperature GO

Ratio of new and old temperature for expansion waves GO

Detachment distance of sphere cone GO

Nose radius of sphere cone GO

Detachment distance of cylinder-wedge GO

Nose radius of cylinder-wedge GO

what is a shock wave

Shock wave, strong pressure wave in any elastic medium such as air, water, or a solid substance, produced by supersonic aircraft, explosions, lightning, or other phenomena that create violent changes in pressure

How to Calculate Mach wave behind the shock with mach infinity?

Mach wave behind the shock with mach infinity calculator uses Mach Number ahead of shock=Mach Number-(local shock velocity/Speed of Sound) to calculate the Mach Number ahead of shock, The Mach wave behind the shock with mach infinity formula is defined as the interrelation between mach no at infinity, local shock velocity and speed of sound at mach infinity. Mach Number ahead of shock and is denoted by M₁ symbol.

How to calculate Mach wave behind the shock with mach infinity using this online calculator? To use this online calculator for Mach wave behind the shock with mach infinity, enter Mach Number (M), local shock velocity (W) and Speed of Sound (𝒶) and hit the calculate button. Here is how the Mach wave behind the shock with mach infinity calculation can be explained with given input values -> -9 = 1-(1000/100).

FAQ

What is Mach wave behind the shock with mach infinity?

The Mach wave behind the shock with mach infinity formula is defined as the interrelation between mach no at infinity, local shock velocity and speed of sound at mach infinity and is represented as M₁=M-(W/𝒶) or Mach Number ahead of shock=Mach Number-(local shock velocity/Speed of Sound). Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound, local shock velocity, is the shock velocity after the shock wave and The speed of sound is defined as the dynamic propagation of sound waves.

How to calculate Mach wave behind the shock with mach infinity?

The Mach wave behind the shock with mach infinity formula is defined as the interrelation between mach no at infinity, local shock velocity and speed of sound at mach infinity is calculated using Mach Number ahead of shock=Mach Number-(local shock velocity/Speed of Sound). To calculate Mach wave behind the shock with mach infinity, you need Mach Number (M), local shock velocity (W) and Speed of Sound (𝒶). With our tool, you need to enter the respective value for Mach Number, local shock velocity and Speed of Sound and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Facebook
Twitter
WhatsApp
Reddit
LinkedIn
E-Mail

Let Others Know

✖

Facebook

Twitter

Copied!