Teaching Limiting Behavior of Plane Oblique Shocks Available to Purchase

Plane oblique shocks are formed in supersonic flows that cause abrupt flow deceleration, compression and turning. This behavior persists up to a maximum flow turning angle, θ_max and a corresponding shock angle β_max for any upstream Mach number M₁ with corresponding Mach angle, μ₁. Beyond the maximum turning angle, the oblique shock becomes detached from the body and forms a bow shock. In teaching limiting behavior of plane oblique shocks, over a broad Mach range, from 1.5 to 5.0, we discover two interesting correlations. The first is on β_max which remains nearly invariant and the second is (μ₁ + θ_max) that remains nearly constant. In air with γ = 1.4, β_max is nearly 65.64° with 0.67° standard deviation and (μ₁ + θ_max) is nearly 53.24° with 0.32° standard deviation angle. Rankine-Hugoniot and Prandtl oblique shock relations are used in theoretical demonstrations of limiting behavior of plane oblique shocks.