Normal Shock Calculator
A stationary shockwave in a calorically-perfect gas is represented by joining two instances of the isentropic flow model via the Rankine-Hugoniot relations. The flow direction is normal to the (flat) shockwave. For such a shockwave to exist the inflow (1) must be supersonic and the outflow (2) subsonic.
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By Specifying Inflow Conditions
- Given an inflow Mach number of 1.M = 2 ⏎ (and the assumed but modifiable γ=1.4 for air), the model infers that the outflow Mach number 2.M ⏎ is 0.6. The model also infers the ratio of inflow to outflow static temperatures and pressures.
- Also 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 ⏎ as well as the mass flow rate per unit area G ⏎ of air that passes through the shock.
By Specifying Outflow Conditions
- Given an outflow Mach number of 2.M = 0.4 ⏎ (close to the minimum inferred from γ how 2.M.minimum ⏎), the model infers that the inflow Mach number 1.M ⏎ is 6.6. The model also infers the ratio of inflow to outflow static temperatures and pressures.
- Also asserting that the outflowing air is at 2.T = 2000 ⏎ K and 2.P = 10 ⏎ bar, the model infers the state of the inflow 1 ⏎ as well as the mass flow rate per unit area G ⏎ of air that passes through the shock.
By Specifying one of {M1 M2} and any two of {P1 T1 ρ1 P2 T2 ρ2}
U can also be asserted, which implies T given M.