Density Downstream of Shock Wave using Continuity Equation Solution

STEP 0: Pre-Calculation Summary
Formula Used
Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock
ρ2 = (ρ1*V1)/V2
This formula uses 4 Variables
Variables Used
Density Behind Normal Shock - (Measured in Kilogram per Cubic Meter) - Density Behind Normal Shock represents the density of a fluid after passing through a normal shock wave.
Density Ahead of Normal Shock - (Measured in Kilogram per Cubic Meter) - Density Ahead of Normal Shock refers to the density of a fluid before encountering a normal shock wave.
Velocity Upstream of Shock - (Measured in Meter per Second) - Velocity Upstream of Shock is the velocity of flow ahead of the shock wave.
Velocity Downstream of Shock - (Measured in Meter per Second) - Velocity Downstream of Shock is the velocity of flow behind the shock wave.
STEP 1: Convert Input(s) to Base Unit
Density Ahead of Normal Shock: 5.4 Kilogram per Cubic Meter --> 5.4 Kilogram per Cubic Meter No Conversion Required
Velocity Upstream of Shock: 80.134 Meter per Second --> 80.134 Meter per Second No Conversion Required
Velocity Downstream of Shock: 79.351 Meter per Second --> 79.351 Meter per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ρ2 = (ρ1*V1)/V2 --> (5.4*80.134)/79.351
Evaluating ... ...
ρ2 = 5.45328477271868
STEP 3: Convert Result to Output's Unit
5.45328477271868 Kilogram per Cubic Meter --> No Conversion Required
FINAL ANSWER
5.45328477271868 5.453285 Kilogram per Cubic Meter <-- Density Behind Normal Shock
(Calculation completed in 00.004 seconds)

Credits

Created by Ravi Khiyani
Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore
Ravi Khiyani has created this Calculator and 200+ more calculators!
Verified by Anshika Arya
National Institute Of Technology (NIT), Hamirpur
Anshika Arya has verified this Calculator and 2500+ 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

Density Downstream of Shock Wave using Continuity Equation Formula

Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock
ρ2 = (ρ1*V1)/V2

What are qualitative changes across the shock waves?

Shock waves are very thin regions in a supersonic flow across which the pressure, density, temperature, and entropy increase, the Mach number, flow velocity, and total pressure decreases, and the total enthalpy stays the same.

How to Calculate Density Downstream of Shock Wave using Continuity Equation?

Density Downstream of Shock Wave using Continuity Equation calculator uses Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock to calculate the Density Behind Normal Shock, The Density Downstream of Shock Wave using Continuity Equation computes the density of a fluid after it has traversed a shock wave, employing the principle of continuity. This formula elucidates how density changes as a fluid moves through the shock wave, taking into account the density ahead of the shock and the velocities upstream and downstream of the shock. Density Behind Normal Shock is denoted by ρ2 symbol.

How to calculate Density Downstream of Shock Wave using Continuity Equation using this online calculator? To use this online calculator for Density Downstream of Shock Wave using Continuity Equation, enter Density Ahead of Normal Shock 1), Velocity Upstream of Shock (V1) & Velocity Downstream of Shock (V2) and hit the calculate button. Here is how the Density Downstream of Shock Wave using Continuity Equation calculation can be explained with given input values -> 9.867551 = (5.4*80.134)/79.351.

FAQ

What is Density Downstream of Shock Wave using Continuity Equation?
The Density Downstream of Shock Wave using Continuity Equation computes the density of a fluid after it has traversed a shock wave, employing the principle of continuity. This formula elucidates how density changes as a fluid moves through the shock wave, taking into account the density ahead of the shock and the velocities upstream and downstream of the shock and is represented as ρ2 = (ρ1*V1)/V2 or Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock. Density Ahead of Normal Shock refers to the density of a fluid before encountering a normal shock wave, Velocity Upstream of Shock is the velocity of flow ahead of the shock wave & Velocity Downstream of Shock is the velocity of flow behind the shock wave.
How to calculate Density Downstream of Shock Wave using Continuity Equation?
The Density Downstream of Shock Wave using Continuity Equation computes the density of a fluid after it has traversed a shock wave, employing the principle of continuity. This formula elucidates how density changes as a fluid moves through the shock wave, taking into account the density ahead of the shock and the velocities upstream and downstream of the shock is calculated using Density Behind Normal Shock = (Density Ahead of Normal Shock*Velocity Upstream of Shock)/Velocity Downstream of Shock. To calculate Density Downstream of Shock Wave using Continuity Equation, you need Density Ahead of Normal Shock 1), Velocity Upstream of Shock (V1) & Velocity Downstream of Shock (V2). With our tool, you need to enter the respective value for Density Ahead of Normal Shock, Velocity Upstream of Shock & Velocity Downstream of Shock 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 Behind Normal Shock?
In this formula, Density Behind Normal Shock uses Density Ahead of Normal Shock, Velocity Upstream of Shock & Velocity Downstream of Shock. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • 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)
  • Density Behind Normal Shock = Density Ahead of Normal Shock*(((Specific Heat Ratio+1)*Mach Number^2)/(2+(Specific Heat Ratio-1)*Mach Number^2))
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!