Compressible Flow Calculator

This tool works the isentropic relations for compressible flow of a perfect gas, with the ratio of specific heats and the specific gas constant entered rather than read from a built-in gas table. Give it a Mach number and it returns the stagnation to static ratios for temperature, pressure and density, the area ratio A over A star, the speed of sound, the velocity, and the Mach and Prandtl-Meyer angles above Mach 1. A second action takes a reservoir pressure and temperature with a throat area and returns the mass flow, saying whether the nozzle is choked and what back pressure would choke it. A third goes the other way, from a ratio to the Mach number, and gives both branches of the area ratio. The relations assume no friction, no heat transfer and no shock, so none of the stagnation pressures carry across a shock wave.