Static Pressure behind Normal Shock using Normal Shock Momentum Equation Solution

STEP 0: Pre-Calculation Summary
Formula Used
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
P2 = P1+ρ1*V1^2-ρ2*V2^2
This formula uses 6 Variables
Variables Used
Static pressure Behind Normal shock - (Measured in Pascal) - Static Pressure Behind Normal Shock denotes the pressure of a fluid after passing through a normal shock wave.
Static Pressure Ahead of Normal Shock - (Measured in Pascal) - Static Pressure Ahead of Normal Shock is the pressure in the upstream direction of shock.
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.
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.
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
Static Pressure Ahead of Normal Shock: 65.374 Pascal --> 65.374 Pascal No Conversion Required
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
Density Behind Normal Shock: 5.5 Kilogram per Cubic Meter --> 5.5 Kilogram per Cubic Meter 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
P2 = P11*V1^2-ρ2*V2^2 --> 65.374+5.4*80.134^2-5.5*79.351^2
Evaluating ... ...
P2 = 110.050356900007
STEP 3: Convert Result to Output's Unit
110.050356900007 Pascal --> No Conversion Required
FINAL ANSWER
110.050356900007 110.0504 Pascal <-- Static pressure Behind Normal shock
(Calculation completed in 00.019 seconds)

Credits

Created by Shikha Maurya
Indian Institute of Technology (IIT), Bombay
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Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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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

Static Pressure behind Normal Shock using Normal Shock Momentum Equation Formula

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
P2 = P1+ρ1*V1^2-ρ2*V2^2

What is normal Shock?

Normal shock is a shock wave that is normal to the upstream flow. The flow properties change drastically across the normal shock.

What is upstream and downstream flow?

The flow ahead of the shock or incoming flow is called upstream flow and flow behind the shock is the downstream flow.

How to Calculate Static Pressure behind Normal Shock using Normal Shock Momentum Equation?

Static Pressure behind Normal Shock using Normal Shock Momentum Equation calculator uses 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 to calculate the Static pressure Behind Normal shock, The Static Pressure behind Normal Shock using Normal Shock Momentum Equation calculates the static pressure of a fluid behind a normal shock wave by applying the Normal Shock Momentum Equation. This formula incorporates parameters such as the static pressure ahead of the shock, the density ahead of the shock, and the velocities upstream and downstream of the shock. It provides valuable insights into the change in static pressure resulting from the passage of the shock wave. Static pressure Behind Normal shock is denoted by P2 symbol.

How to calculate Static Pressure behind Normal Shock using Normal Shock Momentum Equation using this online calculator? To use this online calculator for Static Pressure behind Normal Shock using Normal Shock Momentum Equation, enter Static Pressure Ahead of Normal Shock (P1), Density Ahead of Normal Shock 1), Velocity Upstream of Shock (V1), Density Behind Normal Shock 2) & Velocity Downstream of Shock (V2) and hit the calculate button. Here is how the Static Pressure behind Normal Shock using Normal Shock Momentum Equation calculation can be explained with given input values -> 78969.18 = 65.374+5.4*80.134^2-5.5*79.351^2 .

FAQ

What is Static Pressure behind Normal Shock using Normal Shock Momentum Equation?
The Static Pressure behind Normal Shock using Normal Shock Momentum Equation calculates the static pressure of a fluid behind a normal shock wave by applying the Normal Shock Momentum Equation. This formula incorporates parameters such as the static pressure ahead of the shock, the density ahead of the shock, and the velocities upstream and downstream of the shock. It provides valuable insights into the change in static pressure resulting from the passage of the shock wave and is represented as P2 = P11*V1^2-ρ2*V2^2 or 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. Static Pressure Ahead of Normal Shock is the pressure in the upstream direction 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, Density Behind Normal Shock represents the density of a fluid after passing through a normal shock wave & Velocity Downstream of Shock is the velocity of flow behind the shock wave.
How to calculate Static Pressure behind Normal Shock using Normal Shock Momentum Equation?
The Static Pressure behind Normal Shock using Normal Shock Momentum Equation calculates the static pressure of a fluid behind a normal shock wave by applying the Normal Shock Momentum Equation. This formula incorporates parameters such as the static pressure ahead of the shock, the density ahead of the shock, and the velocities upstream and downstream of the shock. It provides valuable insights into the change in static pressure resulting from the passage of the shock wave is calculated using 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. To calculate Static Pressure behind Normal Shock using Normal Shock Momentum Equation, you need Static Pressure Ahead of Normal Shock (P1), Density Ahead of Normal Shock 1), Velocity Upstream of Shock (V1), Density Behind Normal Shock 2) & Velocity Downstream of Shock (V2). With our tool, you need to enter the respective value for Static Pressure Ahead of Normal Shock, Density Ahead of Normal Shock, Velocity Upstream of Shock, Density Behind Normal 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 Static pressure Behind Normal shock?
In this formula, Static pressure Behind Normal shock uses Static Pressure Ahead of Normal Shock, Density Ahead of Normal Shock, Velocity Upstream of Shock, Density Behind Normal Shock & Velocity Downstream of Shock. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • 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))
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