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Compressible Flow Calculator | Engineering Database

Compressible Flow Calculator

aerospace

Calculates isentropic, normal shock, Fanno, and Rayleigh flow properties for a given Mach number and specific-heat ratio. Provides both analytical results and table interpolation for cross-verification. Optionally computes ISA atmospheric conditions at a given altitude.

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Flow Type*

Type of compressible flow analysis. 'isentropic' for isentropic relations, 'normal_shock' for normal shock (requires M >= 1), 'fanno' for adiabatic flow with friction, 'rayleigh' for frictionless flow with heat addition.

Mach Number*

Freestream Mach number. Subsonic: 0-0.8, transonic: 0.8-1.2, supersonic: 1.2-5, hypersonic: >5. Normal shock requires M >= 1.0.

Gamma

Specific heat ratio (Cp/Cv). Air at standard conditions: 1.4. Combustion gases: ~1.3. Monatomic gases (He, Ar): 1.667. Standard values: 1.4 (air/N2), 1.3 (CO2/steam), 1.67 (He/Ar). If omitted, defaults to 1.4 (air).

Altitude M

Geometric altitude in meters for ISA atmospheric property calculation (temperature, pressure, density, speed of sound). Valid for troposphere: 0-11,000 m. If provided, enables ISA atmospheric property output and velocity in m/s.

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Reference data

This calculator pulls live values from the following engineering reference tables in the database.

compressible flow

About this calculator

Compressible Flow Calculator is part of the Engineering Database calculator suite. Each tool runs deterministic calculations against authoritative reference data and code-compliant methods, so results are reproducible and traceable to source standards.

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