As an aging ex-NASA engineer, it strikes me that none of the muzzle brakes that I have seen on the market today appear to have been designed with proper nozzle theory.
Exhaust gases exiting from the muzzle are clearly supersonic and choked. Every brake I've seen so far uses straight-sided holes, which has to be the least-efficient supersonic nozzle possible. At the least, the exit area should be greater than the throat.
Effective supersonic flow nozzle designs use converging-diverging cross-sections which maximize thrust available from the high-enthalpy conditions (pressure, velocity) in the barrel. The pressure rise across the shock could be used effectively to add a lot more thrust (i.e. reduction in recoil and muzzle rise) than current designs.
This is rocket science, admittedly, but for gosh sakes the converging-diverging nozzle was invented in the late 19th century ("de Laval" nozzle). Can't we do better than some hick design with holes drilled and pointed backwards?
Exhaust gases exiting from the muzzle are clearly supersonic and choked. Every brake I've seen so far uses straight-sided holes, which has to be the least-efficient supersonic nozzle possible. At the least, the exit area should be greater than the throat.
Effective supersonic flow nozzle designs use converging-diverging cross-sections which maximize thrust available from the high-enthalpy conditions (pressure, velocity) in the barrel. The pressure rise across the shock could be used effectively to add a lot more thrust (i.e. reduction in recoil and muzzle rise) than current designs.
This is rocket science, admittedly, but for gosh sakes the converging-diverging nozzle was invented in the late 19th century ("de Laval" nozzle). Can't we do better than some hick design with holes drilled and pointed backwards?