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Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator

Easily calculate and compute normal shock wave downstream mach number & total pressure loss calculator with accurate equations, live formulas, and expert guidance.

Must be supersonic (M₁ > 1.0).

Air γ = 1.40.

Calculated Result
0.58 Mach

Downstream Mach (M₂)

Downstream Mach (M₂)

0.58 Mach

Downstream Mach M2

0.577

Static Pressure Ratio P2 Over P1

4.5

Static Temperature Ratio T2 Over T1

1.69

Total Pressure Recovery P02 Over P01

0.721

0.58 — Mach

Calculation Breakdown

  1. Applied FormulaSolves the Rankine-Hugoniot normal shock equations to calculate the subsonic downstream Mach number (M₂), static pressure jump, and total pressure recovery (P₀₂/P₀₁).M_2 = \sqrt{\frac{2 + (\gamma - 1)M_1^2}{2\gamma M_1^2 - (\gamma - 1)}}

Normal Shock Wave Relations Metric Output

Interactive visualization based on your current inputs

Calculated Value
0.00.30.50.81.0Downstream Mach (M₂)

What Is the Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator?

This tool computes normal shock wave downstream mach number & total pressure loss calculator with high precision arithmetic.

How Does the Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator Work?

Solves the Rankine-Hugoniot normal shock equations to calculate the subsonic downstream Mach number (M₂), static pressure jump, and total pressure recovery (P₀₂/P₀₁).

Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator Formula & Variables

The core mathematical equation utilized by this calculator is expressed as:

M2=2+(γ−1)M122γM12−(γ−1)M_2 = \sqrt{\frac{2 + (\gamma - 1)M_1^2}{2\gamma M_1^2 - (\gamma - 1)}}

Solves the Rankine-Hugoniot normal shock equations to calculate the subsonic downstream Mach number (M₂), static pressure jump, and total pressure recovery (P₀₂/P₀₁).

How to Use the Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator

  1. Enter your parameters into the designated input fields to calculate the result immediately.

Step-by-Step Example Calculation

Normal Shock Wave Downstream Mach Number & Total Pressure Loss Calculator Example

Input Values:

upstreamMachM1:2
ratioOfSpecificHeatsGamma:1.4
Worked Steps: Sample evaluation based on standard reference conditions.

Understanding Your Result

The calculated primary figure indicates the optimal or required Mach.

Factors That Affect the Result

  • Measurement tolerances, operational variance, and real-world conditions.

When Should You Use This Calculator?

  • Everyday budgeting, technical homework, professional estimation, and household projects.

Assumptions & Limitations

  • Assumes standard atmospheric or environmental parameters unless specified.

Frequently Asked Questions

Calculation Accuracy & Reference Note

Double-precision IEEE 754 arithmetic with validated empirical constants.

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