Analyze supersonic flow over a wedge or corner using the θ-β-M relation.
Input Parameters
Calculation Results
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About this calculator
Quick Reference
M₁Upstream Mach Number
βShock Wave Angle
θFlow Deflection Angle
γRatio of Specific Heats
Overview
This calculator solves the oblique shock θ-β-M relation, which describes the relationship between the upstream Mach number, the shock wave angle, and the flow deflection angle.
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Pro Tips
For a given Mach number and deflection angle, there are typically two possible shock angles: a 'weak' shock and a 'strong' shock. This calculator provides the weak shock solution as it is most common in external flows.
The value of γ is typically 1.4 for air.
If the deflection angle θ is too large for a given Mach number, the shock will detach (become a bow shock).
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Fun Facts
"Oblique shocks occur when supersonic flow encounters a wedge or a concave corner."
"As Mach number increases, the maximum possible deflection angle θ also increases."
"The 'Mach angle' is the case where the shock wave is infinitesimally weak (μ = arcsin(1/M))."
