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Oblique Shock Calculator
Calculate supersonic oblique shock wave properties ($M_2$, pressure and density ratios)
Formula: Normal Mach number $M_{1n} = M_1 \sin\beta$.
Deflection angle relation: $\tan \theta = 2 \cot \beta \frac{M_1^2 \sin^2 \beta - 1}{M_1^2(\gamma + \cos 2\beta) + 2}$.
Deflection angle relation: $\tan \theta = 2 \cot \beta \frac{M_1^2 \sin^2 \beta - 1}{M_1^2(\gamma + \cos 2\beta) + 2}$.
Aerodynamic Parameters
Calculation Results
⚠️ For compressible aerodynamics and aerospace education reference only. Assumes ideal gas and steady 2D planar shock.