Compressible Aerodynamics Calculator

Calculate Mach number, shockwave properties, nozzle flows, and more for compressible fluid dynamics analysis

Velocity i

Temperature i

Specific Heat Ratio (γ) i

Gas Constant (R) i

Flow Regime

Subsonic M < 0.8

Transonic 0.8 ≤ M ≤ 1.2

Supersonic 1.2 < M < 5

Hypersonic M ≥ 5

M = 0.00

Upstream Mach Number (M₁) i

Specific Heat Ratio (γ) i

Nozzle Type i

Area Ratio (A/A*) i

Specific Heat Ratio (γ) i

Back Pressure Ratio (Pₐ/P₀) i

Mach Condition 1 i

Mach Condition 2 i

Specific Heat Ratio (γ) i

Compressible Flow Results

Mach Number

P/P₀

Pressure Ratio

T/T₀

Temperature Ratio

ρ/ρ₀

Density Ratio

A/A*

Area Ratio

Compressibility Factor

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