Characteristic Mach Number behind Shock Solution

STEP 0: Pre-Calculation Summary
Formula Used
Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock
M2cr = 1/M1cr
This formula uses 2 Variables
Variables Used
Characteristic Mach Number Behind Shock - Characteristic Mach number behind shock is the speed of an object to speed of sound at the sonic condition after passing through the shockwave.
Characteristic Mach Number Ahead of Shock - Characteristic Mach Number Ahead of Shock is the speed of an object relative to speed of sound at the sonic condition before the shockwave has occurred.
STEP 1: Convert Input(s) to Base Unit
Characteristic Mach Number Ahead of Shock: 3 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
M2cr = 1/M1cr --> 1/3
Evaluating ... ...
M2cr = 0.333333333333333
STEP 3: Convert Result to Output's Unit
0.333333333333333 --> No Conversion Required
FINAL ANSWER
0.333333333333333 0.333333 <-- Characteristic Mach Number Behind Shock
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ more calculators!

15 Downstream Shock Waves Calculators

Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula
Go Stagnation Pressure Behind Normal Shock = Static Pressure Ahead of Normal Shock*((1-Specific Heat Ratio+2*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2)/(Specific Heat Ratio+1))*(((Specific Heat Ratio+1)^2*Mach Number Ahead of Normal Shock^2)/(4*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-2*(Specific Heat Ratio-1)))^((Specific Heat Ratio)/(Specific Heat Ratio-1))
Static Temperature behind Normal Shock for given Upstream Temperature and Mach Number
Go Temperature Behind Normal Shock = Temperature Ahead of Normal Shock*((1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1))/((Specific Heat Ratio+1)*(Mach Number Ahead of Normal Shock^2)/(2+(Specific Heat Ratio-1)*Mach Number Ahead of Normal Shock^2)))
Static Enthalpy behind Normal Shock for given Upstream Enthalpy and Mach Number
Go Enthalpy Behind Normal Shock = Enthalpy Ahead of Normal Shock*(1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1))/((Specific Heat Ratio+1)*(Mach Number Ahead of Normal Shock^2)/(2+(Specific Heat Ratio-1)*Mach Number Ahead of Normal Shock^2))
Mach Number behind Shock
Go Mach Number Behind Normal Shock = ((2+Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-Mach Number Ahead of Normal Shock^2)/(2*Specific Heat Ratio*Mach Number Ahead of Normal Shock^2-Specific Heat Ratio+1))^(1/2)
Velocity behind Normal Shock by Normal Shock Momentum Equation
Go Velocity Downstream of Shock = sqrt((Static Pressure Ahead of Normal Shock-Static pressure Behind Normal shock+Density Ahead of Normal Shock*Velocity Upstream of Shock^2)/Density Behind Normal Shock)
Density behind Normal Shock using Normal Shock Momentum Equation
Go Density Behind Normal Shock = (Static Pressure Ahead of Normal Shock+Density Ahead of Normal Shock*Velocity Upstream of Shock^2-Static pressure Behind Normal shock)/(Velocity Downstream of Shock^2)
Static Pressure behind Normal Shock using Normal Shock Momentum Equation
Go Static pressure Behind Normal shock = Static Pressure Ahead of Normal Shock+Density Ahead of Normal Shock*Velocity Upstream of Shock^2-Density Behind Normal Shock*Velocity Downstream of Shock^2
Density behind Normal Shock given Upstream Density and Mach Number
Go Density Behind Normal Shock = Density Ahead of Normal Shock*(((Specific Heat Ratio+1)*Mach Number^2)/(2+(Specific Heat Ratio-1)*Mach Number^2))
Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number
Go Static pressure Behind Normal shock = Static Pressure Ahead of Normal Shock*(1+((2*Specific Heat Ratio)/(Specific Heat Ratio+1))*(Mach Number Ahead of Normal Shock^2-1))
Velocity behind Normal Shock from Normal Shock Energy Equation
Go Velocity Downstream of Shock = sqrt(2*(Enthalpy Ahead of Normal Shock+(Velocity Upstream of Shock^2)/2-Enthalpy Behind Normal Shock))
Velocity behind Normal Shock
Go Velocity Downstream of Shock = Velocity Upstream of Shock/((Specific Heat Ratio+1)/((Specific Heat Ratio-1)+2/(Mach Number^2)))
Enthalpy behind Normal Shock from Normal Shock Energy Equation
Go Enthalpy Behind Normal Shock = Enthalpy Ahead of Normal Shock+(Velocity Upstream of Shock^2-Velocity Downstream of Shock^2)/2
Flow Velocity Downstream of Shock Wave using Continuity Equation
Go Velocity Downstream of Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Density Behind Normal Shock
Density Downstream of Shock Wave using Continuity Equation
Go Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock
Characteristic Mach Number behind Shock
Go Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock

Characteristic Mach Number behind Shock Formula

Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock
M2cr = 1/M1cr

What is a Characteristic Mach number?

Characteristic Mach number is defined as the speed of an object to the speed of sound at the sonic condition.

How to Calculate Characteristic Mach Number behind Shock?

Characteristic Mach Number behind Shock calculator uses Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock to calculate the Characteristic Mach Number Behind Shock, Characteristic Mach Number behind Shock is the reciprocal of Characteristic Mach Number ahead of shock. Characteristic Mach Number Behind Shock is denoted by M2cr symbol.

How to calculate Characteristic Mach Number behind Shock using this online calculator? To use this online calculator for Characteristic Mach Number behind Shock, enter Characteristic Mach Number Ahead of Shock (M1cr) and hit the calculate button. Here is how the Characteristic Mach Number behind Shock calculation can be explained with given input values -> 0.5 = 1/3.

FAQ

What is Characteristic Mach Number behind Shock?
Characteristic Mach Number behind Shock is the reciprocal of Characteristic Mach Number ahead of shock and is represented as M2cr = 1/M1cr or Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock. Characteristic Mach Number Ahead of Shock is the speed of an object relative to speed of sound at the sonic condition before the shockwave has occurred.
How to calculate Characteristic Mach Number behind Shock?
Characteristic Mach Number behind Shock is the reciprocal of Characteristic Mach Number ahead of shock is calculated using Characteristic Mach Number Behind Shock = 1/Characteristic Mach Number Ahead of Shock. To calculate Characteristic Mach Number behind Shock, you need Characteristic Mach Number Ahead of Shock (M1cr). With our tool, you need to enter the respective value for Characteristic Mach Number Ahead of Shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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