## Pressure Ratio across Oblique shock Solution

STEP 0: Pre-Calculation Summary
Formula Used
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)
Pshockratio = 1+((2*κ)/(κ+1))*((Mn1^2)-1)
This formula uses 3 Variables
Variables Used
Pressure ratio across shock - Pressure ratio across shock is the ratio of downstream to upstream pressure across shock.
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.
Component of upstream mach normal to oblique shock - Component of upstream mach normal to oblique shock is that component of upstream Mach number which is normal to oblique shockwave.
STEP 1: Convert Input(s) to Base Unit
Specific Heat Ratio Dynamic: 1.392758 --> No Conversion Required
Component of upstream mach normal to oblique shock: 2 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Pshockratio = 1+((2*κ)/(κ+1))*((Mn1^2)-1) --> 1+((2*1.392758)/(1.392758+1))*((2^2)-1)
Evaluating ... ...
Pshockratio = 4.49243341783833
STEP 3: Convert Result to Output's Unit
4.49243341783833 --> No Conversion Required
4.49243341783833 <-- Pressure ratio across shock
(Calculation completed in 00.000 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!
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PSG College of Technology (PSGCT), Coimbatore
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## < 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 Ratio across Oblique shock Formula

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)
Pshockratio = 1+((2*κ)/(κ+1))*((Mn1^2)-1)

## Which inlet design of supersonic jet engine is preferable?

A normal shock inlet forms a normal shock ahead of the inlet, with an attendant large loss in total pressure. In contrast, an oblique shock inlet creates an oblique shock wave, and the flow subsequently passes through a relatively weak normal shock at the lip of the inlet. For the same flight conditions (Mach number and altitude), the total pressure loss for the oblique shock inlet is less than for a normal shock inlet. Hence, everything else being equal, the resulting engine thrust will be higher for the oblique shock inlet. Therefore, oblique shock inlets are preffered.

## What does total pressure indicates?

The total pressure is an indicator of how much useful work can be done by gas. Everything else being equal, the higher the total pressure, the more useful is the flow.

## How to Calculate Pressure Ratio across Oblique shock?

Pressure Ratio across Oblique shock calculator uses 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) to calculate the Pressure ratio across shock, Pressure ratio across oblique shock formula is obtained by substituting the normal component of upstream Mach no. in the pressure ratio formula for the normal shock. Pressure ratio across shock is denoted by Pshockratio symbol.

How to calculate Pressure Ratio across Oblique shock using this online calculator? To use this online calculator for Pressure Ratio across Oblique shock, enter Specific Heat Ratio Dynamic (κ) & Component of upstream mach normal to oblique shock (Mn1) and hit the calculate button. Here is how the Pressure Ratio across Oblique shock calculation can be explained with given input values -> 4.492433 = 1+((2*1.392758)/(1.392758+1))*((2^2)-1).

### FAQ

What is Pressure Ratio across Oblique shock?
Pressure ratio across oblique shock formula is obtained by substituting the normal component of upstream Mach no. in the pressure ratio formula for the normal shock and is represented as Pshockratio = 1+((2*κ)/(κ+1))*((Mn1^2)-1) or 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). The Specific Heat Ratio Dynamic is the ratio of the heat capacity at constant pressure to heat capacity at constant volume & Component of upstream mach normal to oblique shock is that component of upstream Mach number which is normal to oblique shockwave.
How to calculate Pressure Ratio across Oblique shock?
Pressure ratio across oblique shock formula is obtained by substituting the normal component of upstream Mach no. in the pressure ratio formula for the normal shock is calculated using 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). To calculate Pressure Ratio across Oblique shock, you need Specific Heat Ratio Dynamic (κ) & Component of upstream mach normal to oblique shock (Mn1). With our tool, you need to enter the respective value for Specific Heat Ratio Dynamic & Component of upstream mach normal to oblique 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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