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Pressure behind expansion fan Calculator

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✖Pressure ahead expansion fan is the pressure in the upstream direction of the expansion fan.ⓘ Pressure ahead expansion fan [P1]
+10%
-10%
✖The Specific Heat Ratio Dynamic is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.ⓘ Specific Heat Ratio Dynamic [κ]
+10%
-10%
✖Mach no. ahead expansion fan is the Mach number of the upstream flow.ⓘ Mach no. ahead expansion fan [M 1]
+10%
-10%
✖Mach no. behind expansion fan is the Mach number of downstream flow across expansion fan.ⓘ Mach no. behind expansion fan [M2]
+10%
-10%
✖Pressure behind expansion fan is the pressure in the downstream direction of the expansion fan.ⓘ Pressure behind expansion fan [P2]
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Pressure behind expansion fan Solution

STEP 0: Pre-Calculation Summary
Formula Used
Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1))
P2 = P1*((1+0.5*(κ-1)*(M 1^2))/(1+0.5*(κ-1)*(M2^2)))^((κ)/(κ-1))
This formula uses 5 Variables
Variables Used
Pressure behind expansion fan - (Measured in Pascal) - Pressure behind expansion fan is the pressure in the downstream direction of the expansion fan.
Pressure ahead expansion fan - (Measured in Pascal) - Pressure ahead expansion fan is the pressure in the upstream direction of the expansion fan.
Specific Heat Ratio Dynamic - The Specific Heat Ratio Dynamic is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.
Mach no. ahead expansion fan - Mach no. ahead expansion fan is the Mach number of the upstream flow.
Mach no. behind expansion fan - Mach no. behind expansion fan is the Mach number of downstream flow across expansion fan.
STEP 1: Convert Input(s) to Base Unit
Pressure ahead expansion fan: 45 Pascal --> 45 Pascal No Conversion Required
Specific Heat Ratio Dynamic: 1.392758 --> No Conversion Required
Mach no. ahead expansion fan: 5 --> No Conversion Required
Mach no. behind expansion fan: 6 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
P2 = P1*((1+0.5*(κ-1)*(M 1^2))/(1+0.5*(κ-1)*(M2^2)))^((κ)/(κ-1)) --> 45*((1+0.5*(1.392758-1)*(5^2))/(1+0.5*(1.392758-1)*(6^2)))^((1.392758)/(1.392758-1))
Evaluating ... ...
P2 = 14.9075460281238
STEP 3: Convert Result to Output's Unit
14.9075460281238 Pascal --> No Conversion Required
FINAL ANSWER
14.9075460281238 Pascal <-- Pressure behind expansion fan
(Calculation completed in 00.016 seconds)
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Credits

Created by Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has created this Calculator and 100+ more calculators!
Verified by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has verified this Calculator and 100+ more calculators!

10+ Oblique Shock and Expansion Waves Calculators

Temperature behind oblique shock for given upstream temperature and normal upstream Mach number
Temperature behind shock = Temperature ahead of shock*((1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1))/((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2))))) Go
Temperature Ratio across Oblique Shock
Temperature ratio across shock = (1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1))/((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2)))) Go
Pressure behind expansion fan
Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)) Go
Component of downstream Mach number normal to oblique shock for given normal upstream Mach number
Downstream Mach Normal to Oblique Shock = sqrt((1+0.5*((Specific Heat Ratio Dynamic-1)*Component of upstream mach normal to oblique shock^2))/(Specific Heat Ratio Dynamic*Component of upstream mach normal to oblique shock^2-0.5*(Specific Heat Ratio Dynamic-1))) Go
Pressure Ratio across Expansion Fan
Pressure ratio across expansion fan = ((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)) Go
Density behind oblique shock for given upstream density and normal upstream Mach number
Density behind shock = Density ahead of shock*((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2)))) Go
Density Ratio across Oblique Shock
Density ratio across shock = (Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2))) Go
Pressure behind oblique shock for given upstream pressure and normal upstream Mach number
Static pressure behind shock = Static pressure ahead of shock*(1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1)) Go
Temperature Ratio across Expansion Fan
Temperature ratio across expansion fan = (1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)) Go
Pressure Ratio across Oblique shock
Pressure ratio across shock = 1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1) Go

Pressure behind expansion fan Formula

Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1))
P2 = P1*((1+0.5*(κ-1)*(M 1^2))/(1+0.5*(κ-1)*(M2^2)))^((κ)/(κ-1))

When an expansion fan is formed?

When a flow is turned away from itself, an expansion fan is formed. The expansion through the wave takes place across a continuous succession of Mach waves and entropy change is zero for each Mach wave, hence the expansion is isentropic.

What is forward and rearward Mach angle?

The forward Machangle is the angle formed between the forward Mach line and upstream direction of the flow. The rearward Mach angle is the angle formed between the rearward Mach line and downstream flow direction (parallel to convex corner).

How to Calculate Pressure behind expansion fan?

Pressure behind expansion fan calculator uses Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)) to calculate the Pressure behind expansion fan, The Pressure behind expansion fan formula is defined as the product of upstream static pressure ahead of expansion fan to the ratio of static to stagnation pressure ratio downstream to upstream across the expansion fan. Pressure behind expansion fan is denoted by P2 symbol.

How to calculate Pressure behind expansion fan using this online calculator? To use this online calculator for Pressure behind expansion fan, enter Pressure ahead expansion fan (P1), Specific Heat Ratio Dynamic (κ), Mach no. ahead expansion fan (M 1) & Mach no. behind expansion fan (M2) and hit the calculate button. Here is how the Pressure behind expansion fan calculation can be explained with given input values -> 14.90755 = 45*((1+0.5*(1.392758-1)*(5^2))/(1+0.5*(1.392758-1)*(6^2)))^((1.392758)/(1.392758-1)).

FAQ

What is Pressure behind expansion fan?
The Pressure behind expansion fan formula is defined as the product of upstream static pressure ahead of expansion fan to the ratio of static to stagnation pressure ratio downstream to upstream across the expansion fan and is represented as P2 = P1*((1+0.5*(κ-1)*(M 1^2))/(1+0.5*(κ-1)*(M2^2)))^((κ)/(κ-1)) or Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)). Pressure ahead expansion fan is the pressure in the upstream direction of the expansion fan, The Specific Heat Ratio Dynamic is the ratio of the heat capacity at constant pressure to heat capacity at constant volume, Mach no. ahead expansion fan is the Mach number of the upstream flow & Mach no. behind expansion fan is the Mach number of downstream flow across expansion fan.
How to calculate Pressure behind expansion fan?
The Pressure behind expansion fan formula is defined as the product of upstream static pressure ahead of expansion fan to the ratio of static to stagnation pressure ratio downstream to upstream across the expansion fan is calculated using Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)). To calculate Pressure behind expansion fan, you need Pressure ahead expansion fan (P1), Specific Heat Ratio Dynamic (κ), Mach no. ahead expansion fan (M 1) & Mach no. behind expansion fan (M2). With our tool, you need to enter the respective value for Pressure ahead expansion fan, Specific Heat Ratio Dynamic, Mach no. ahead expansion fan & Mach no. behind expansion fan 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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