# 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.

Press **⏎** to see the model. Try your own inputs or the examples below. Refresh your browser to clear results.

## 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 {M_{1 }M_{2}} and any two of {P_{1 }T_{1 }ρ_{1 }P_{2 }T_{2 }ρ_{2}}

U can also be asserted, which implies T given M.