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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