Mach wave behind the shock Calculator

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✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the airⓘ Freestream Velocity [V_∞]			+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 behind shock is the Mach number over the body after a shockwave has occurredⓘ Mach wave behind the shock [M₂]

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Mach wave behind the shock

Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ 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

Maximum Pressure coefficient

The maximum pressure coefficient=(Total pressure-Pressure)/(0.5*Density*(Freestream Velocity)^2) GO

Change in velocity for hypersonic flow in x direction

Change in velocity for hypersonic flow=Fluid Velocity-Freestream Velocity GO

Non-dimensional pressure

Non-dimensionalized Pressure=Pressure/(Density*(Freestream Velocity)^2) GO

Weight of aircraft for given required power

Weight=Power*lift coefficient/(Freestream Velocity*Drag Coefficient) GO

Power required for given aerodynamic coefficients

Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO

Isentropic compressibility for given density and speed of sound

Isentropic compressibility=1/(Density*(Speed of Sound^2)) GO

Power required for given required thrust

Power=Freestream Velocity*Thrust of an aircraft GO

Thrust required for given required power

Thrust of an aircraft=Power/Freestream Velocity GO

Mach Number

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

Power required for given total drag

Power=Drag Force*Freestream Velocity GO

Total drag for given required power

Drag Force=Power/Freestream Velocity GO

< 1 Other formulas that calculate the same Output

Mach Number behind the shock

Mach Number behind shock=((2+(Specific heat ratio*(Mach Number ahead of shock^2))-(Mach Number ahead of shock^2))/((2*Specific heat ratio*(Mach Number ahead of shock^2))-Specific heat ratio+1))^(1/2) GO

Mach wave behind the shock Formula

Mach Number behind shock=(Freestream Velocity-local shock velocity)/Speed of Sound
M<sub>2</sub>=(V<sub>∞</sub>-W)/𝒶

More formulas

Grid point calculation for shock waves GO

Mach wave behind the shock with mach infinity 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

wWat 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?

Mach wave behind the shock calculator uses Mach Number behind shock=(Freestream Velocity-local shock velocity)/Speed of Sound to calculate the Mach Number behind shock, The Mach wave behind the shock formula is defined as the ratio of freestream velocity minus the local shock velocity to the speed of sound. Mach Number behind shock and is denoted by M₂ symbol.

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

FAQ

What is Mach wave behind the shock?

The Mach wave behind the shock formula is defined as the ratio of freestream velocity minus the local shock velocity to the speed of sound and is represented as M₂=(V_∞-W)/𝒶 or Mach Number behind shock=(Freestream Velocity-local shock velocity)/Speed of Sound. The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air, 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?

The Mach wave behind the shock formula is defined as the ratio of freestream velocity minus the local shock velocity to the speed of sound is calculated using Mach Number behind shock=(Freestream Velocity-local shock velocity)/Speed of Sound. To calculate Mach wave behind the shock, you need Freestream Velocity (V_∞), local shock velocity (W) and Speed of Sound (𝒶). With our tool, you need to enter the respective value for Freestream Velocity, 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.

How many ways are there to calculate Mach Number behind shock?

In this formula, Mach Number behind shock uses Freestream Velocity, local shock velocity and Speed of Sound. We can use 1 other way(s) to calculate the same, which is/are as follows -

Mach Number behind shock=((2+(Specific heat ratio*(Mach Number ahead of shock^2))-(Mach Number ahead of shock^2))/((2*Specific heat ratio*(Mach Number ahead of shock^2))-Specific heat ratio+1))^(1/2)

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