Oblique Shock Calculator
An oblique stationary shockwave in a calorically-perfect gas is represented by adding a transverse velocity component to a normal shockwave model. Correspondingly, the static fluid state of the inflow (1) and the outflow (2) are the same as the static fluid state of the normal shock’s inflow (n.1) and outflow (n.2) , but total conditions differ. If the outflow (2) is subsonic then the shock is strong, and if it is supersonic then the shock is weak.
Press ⏎ to see the model. Try your own inputs or the examples below. Refresh your browser to clear results.
By Specifying Inflow Conditions and Flow Deflection Angle
- Given an inflow Mach number of 1.M = 5 ⏎, the assumed but modifiable γ=1.4 for air, and θ = 20° flow deflection angle y ⏎, the model infers that the shockwave angle β b ⏎ is 30°. The model also infers the ratio of inflow to outflow static temperatures and pressures.
- Asserting that the inflowing air is at 1.T = 300 ⏎ K and 1.P = 1 ⏎ bar, the model infers the state of the outflow 2 ⏎. Beware that the mass flow rate per unit area of air 1.G ⏎ is now unequal to 2.G ⏎ because the shock has changed the flow direction.
- To obtain the strong solution (as opposed to the default weak solution), set isStrong = true ⏎.