Temperature Ratio Across a Normal Shock Calculator

Static temperature before the shock (T₁):

Static temperature after the shock (T₂):

Mach Number (M):

Ratio of Specific Heats (γ):

How This Is Calculated

$$ \frac{T_2}{T_1} = \frac{ (1+\frac{\gamma - 1}{2} M_1^2) (\gamma - 1) M_1^2 + 2 }{(\gamma + 1)^2 M_1^2} $$ where:

T₁ = Static temperature before the shock (K)

T₂ = Static temperature after the shock (K)

M₁ = Mach Number (Dimensionless)

γ = Ratio of Specific Heats (Dimensionless)

Assumptions

Flow is steady.
Flow is one-dimensional.
Shock is normal to flow direction.
The fluid behaves as an ideal gas.
Process is adiabatic.

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