# 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

1. 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.
2. 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

1. 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.
2. 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.