Compressible Flow Lab

Normal shocks, oblique shocks, and Prandtl-Meyer fans. Change Mach or turning angle — watch the waves move in real time.

FREESTREAM

M₁ (upstream Mach)2.00

Wedge / Deflection θ8.0°

Max attached shock ~23–28° depending on M₁

PROPERTY JUMPS

β (shock angle)85.03°

M₂0.594

p₂ / p₁4.465

T₂ / T₁1.6814

Mn₁ (normal component)1.992

OBLIQUE SHOCK ON WEDGEβ = 85.0° • M₂ = 0.594

Blue = shock wave. Green = flow after deflection θ. The shock is weaker than a normal shock at same M₁.

Pressure ratio across wave (M₁ = 2.0)

At θ=0 the oblique shock reduces to a Mach wave (p₂/p₁=1). Maximum deflection has a detached shock limit.

Reference: John D. Anderson Jr., Fundamentals of Aerodynamics, 5th Edition, Chapters 8 (Normal & Oblique Shocks) and 9 (Prandtl-Meyer Expansion Waves).
All calculations assume γ = 1.4 (perfect diatomic gas). Entropy rises only across shocks.