Supersonic Oblique Shock (θ-β-M) Calculator
Solve the compressible flow oblique shock θ-β-M relation, downstream Mach number (M2), static and stagnation pressure ratios, and shock detachment limits.
Upstream Mach & Deflection Angle
Oblique Shock Properties & State 2
Shock Wave Angle (β):
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Mn1 = —
Downstream Mach Number (M2):
—
Mn2 = —
Static Pressure Ratio (P2 / P1):
—
Total Pressure Recovery (P02 / P01):
—
Maximum Deflection Angle (θ_max):
—
Shock Attachment Status:
—