Down Stream Mach Number Post author:maridurai Post published:May 3, 2021 Post category:Aerodynamics Calculator / Airplane Performance Calculator / Engineering Calculator / Flight Mechanics Calculator The Mach number of a normal shock wave is always greater than unity in the upstream and less than unity in the downstream, the static pressure always increases across the shock wave Mx= Up Stream Mach Number Tags: aerodynamics calculator, Down Stream Mach Number Read more articles Previous PostDrag of Bypassed Air Next PostGross Thrust Coefficient You Might Also Like Acceleration due to Gravity by Mohit Kudal October 23, 2020 Upstream Dynamic Pressure June 11, 2021 Linearized Supersonic Pressure Coefficient Calculator October 20, 2020