Static Enthalpy Ratio across Normal Shock Calculator

✖The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.ⓘ Specific Heat Ratio [γ]			+10% -10%
✖Mach Number Ahead of Normal Shock represents the velocity of a fluid or airflow relative to the speed of sound before encountering a normal shock wave.ⓘ Mach Number Ahead of Normal Shock [M₁]			+10% -10%

✖Static Enthalpy Ratio Across Normal Shock signifies the ratio of static enthalpies before and after passing through a normal shock wave.ⓘ Static Enthalpy Ratio across Normal Shock [H_r]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Normal Shock Wave Formulas PDF PDF Image

Static Enthalpy Ratio across Normal Shock Solution

STEP 0: Pre-Calculation Summary

Formula Used

Static Enthalpy Ratio Across 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))
H_r = (1+((2*γ)/(γ+1))*(M₁^2-1))/((γ+1)*(M₁^2)/(2+(γ-1)*M₁^2))
This formula uses 3 Variables

Variables Used

Static Enthalpy Ratio Across Normal Shock - Static Enthalpy Ratio Across Normal Shock signifies the ratio of static enthalpies before and after passing through a normal shock wave.
Specific Heat Ratio - The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.
Mach Number Ahead of Normal Shock - Mach Number Ahead of Normal Shock represents the velocity of a fluid or airflow relative to the speed of sound before encountering a normal shock wave.

STEP 1: Convert Input(s) to Base Unit

Specific Heat Ratio: 1.4 --> No Conversion Required
Mach Number Ahead of Normal Shock: 1.49 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

H_r = (1+((2*γ)/(γ+1))*(M₁^2-1))/((γ+1)*(M₁^2)/(2+(γ-1)*M₁^2)) --> (1+((2*1.4)/(1.4+1))*(1.49^2-1))/((1.4+1)*(1.49^2)/(2+(1.4-1)*1.49^2))

Evaluating ... ...

H_r = 1.3135708109995

STEP 3: Convert Result to Output's Unit

1.3135708109995 --> No Conversion Required

FINAL ANSWER

1.3135708109995 ≈ 1.313571 <-- Static Enthalpy Ratio Across Normal Shock

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aerodynamics » Compressible Flow » Normal Shock Wave » Aerospace » Property Change Across Shock Waves » Static Enthalpy Ratio across Normal Shock

Credits

Created by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has created this Calculator and 100+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< Property Change Across Shock Waves Calculators

Density Ratio across Normal Shock

LaTeX Go Density Ratio Across Normal Shock = (Specific Heat Ratio+1)*(Mach Number Ahead of Normal Shock^2)/(2+(Specific Heat Ratio-1)*Mach Number Ahead of Normal Shock^2)

Entropy Change across Normal Shock

LaTeX Go Entropy Change = Specific Gas Constant*ln(Stagnation Pressure Ahead of Normal Shock/Stagnation Pressure Behind Normal Shock)

Pressure Ratio across Normal Shock

LaTeX Go Pressure Ratio Across Normal Shock = 1+(2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number Ahead of Normal Shock^2-1)

Shock Strength

LaTeX Go Shock Strength = ((2*Specific Heat Ratio)/(1+Specific Heat Ratio))*(Mach Number Ahead of Normal Shock^2-1)

Static Enthalpy Ratio across Normal Shock Formula

LaTeX Go

How to obtain static enthalpy ratio across normal shock?

Static enthalpy ratio across a normal shock is obtained as the ratio of static temperature ratio across the normal shock wave.

How to Calculate Static Enthalpy Ratio across Normal Shock?

Static Enthalpy Ratio across Normal Shock calculator uses Static Enthalpy Ratio Across 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)) to calculate the Static Enthalpy Ratio Across Normal Shock, Static Enthalpy Ratio across Normal Shock formula is defined as a measure of the change in enthalpy across a normal shock wave, reflecting the energy transformation and thermodynamic properties of compressible flow in aerospace applications. Static Enthalpy Ratio Across Normal Shock is denoted by H_r symbol.

How to calculate Static Enthalpy Ratio across Normal Shock using this online calculator? To use this online calculator for Static Enthalpy Ratio across Normal Shock, enter Specific Heat Ratio (γ) & Mach Number Ahead of Normal Shock (M₁) and hit the calculate button. Here is how the Static Enthalpy Ratio across Normal Shock calculation can be explained with given input values -> 1.313571 = (1+((2*1.4)/(1.4+1))*(1.49^2-1))/((1.4+1)*(1.49^2)/(2+(1.4-1)*1.49^2)).

FAQ

What is Static Enthalpy Ratio across Normal Shock?

Static Enthalpy Ratio across Normal Shock formula is defined as a measure of the change in enthalpy across a normal shock wave, reflecting the energy transformation and thermodynamic properties of compressible flow in aerospace applications and is represented as H_r = (1+((2*γ)/(γ+1))*(M₁^2-1))/((γ+1)*(M₁^2)/(2+(γ-1)*M₁^2)) or Static Enthalpy Ratio Across 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)). The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume & Mach Number Ahead of Normal Shock represents the velocity of a fluid or airflow relative to the speed of sound before encountering a normal shock wave.

How to calculate Static Enthalpy Ratio across Normal Shock?

Static Enthalpy Ratio across Normal Shock formula is defined as a measure of the change in enthalpy across a normal shock wave, reflecting the energy transformation and thermodynamic properties of compressible flow in aerospace applications is calculated using Static Enthalpy Ratio Across 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)). To calculate Static Enthalpy Ratio across Normal Shock, you need Specific Heat Ratio (γ) & Mach Number Ahead of Normal Shock (M₁). With our tool, you need to enter the respective value for Specific Heat Ratio & Mach Number Ahead of Normal Shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search