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Rankine-Hugoniot Supersonic Normal Shock Pressure Ratio Calculator

Normal shock waves represent abrupt, irreversible discontinuous compressions perpendicular to supersonic fluid flow.

Supersonic approach Mach number (> 1.0)

Ambient freestream static pressure

Calculated Result
246.6 kPa

Downstream Pressure (P2)

Static Pressure Ratio (P2/P1)

5.48

Downstream Mach (M2)

0.547

Calculation Breakdown

  1. Rankine-Hugoniot Normal ShockP2/P1 = 1 + [2γ/(γ+1)](M1² - 1) => 5.48

Pressure Ratio vs Mach

Interactive visualization based on your current inputs

Ratio
0.02.65.27.710Mach 1.5Mach 2.2Mach 3.0Mach NumberP2/P1 Ratio

What Is the Rankine-Hugoniot Supersonic Normal Shock Pressure Ratio Calculator?

Normal shock waves represent abrupt, irreversible discontinuous compressions perpendicular to supersonic fluid flow.

Rankine-Hugoniot relations derive post-shock thermodynamic jumps strictly from conservation of mass, momentum, and energy.

How Does the Rankine-Hugoniot Supersonic Normal Shock Pressure Ratio Calculator Work?

The calculation evaluates user-provided measurements using recognized domain equations, converts between measurement units, and adjusts for real-world efficiency factors.

Rankine-Hugoniot Supersonic Normal Shock Pressure Ratio Calculator Formula & Variables

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

\frac{P_2}{P_1} = 1 + \frac{2 \gamma}{\gamma + 1} (M_1^2 - 1), \quad M_2 = \sqrt{\frac{(\gamma - 1)M_1^2 + 2}{2\gamma M_1^2 - (\gamma - 1)}}

Rankine-Hugoniot normal shock jump conditions.

How to Use the Rankine-Hugoniot Supersonic Normal Shock Pressure Ratio Calculator

  1. Enter your primary measurements in the input fields above.
  2. Select your preferred units (e.g. metric or imperial) if applicable.
  3. Review or adjust operational assumptions such as field efficiency.
  4. Click Calculate to instantly generate the full results breakdown and visual chart.
  5. Use the Reset button at any time to clear the form and test a new scenario.

Step-by-Step Example Calculation

Pitot Tube Ingestion at Mach 2.5

Input Values:

upstreamMachM1:2.5
upstreamPressureP1Kpa:30.0

Understanding Your Result

Your calculated result represents the realistic operational capacity or baseline output under the specified conditions. Comparing theoretical and effective outputs reveals the direct impact of turns, overlap, and practical downtime.

Factors That Affect the Result

Field terrain, operator experience, equipment maintenance, overlap margin, and weather conditions can significantly influence real-world output.

When Should You Use This Calculator?

Use this calculator whenever you need quick, verified estimates for job planning, budgeting, equipment sizing, or project timelines.

Assumptions & Limitations

  • Flow downstream of a normal shock is always subsonic (M2 < 1.0).

Frequently Asked Questions

Calculation Accuracy & Reference Note

This calculator implements verified, deterministic mathematical equations based on published standards. Results should be treated as professional engineering estimates; always verify critical operations with local equipment manuals and site inspections.

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