A thrust recovery outflow valve for use with an aircraft comprising: a first gate having a first aerodynamic surface and a second gate having a second aerodynamic surface, the first gate to move relative to the second gate between an open position to allow fluid flow to atmosphere and a closed position to prevent fluid flow to atmosphere, the first aerodynamic surface of the first gate being spaced from the second aerodynamic surface of the second gate to define a fluid flow passageway having a convergent-divergent shape or profile when the thrust recovery outflow valve is in the open position, the first aerodynamic surface having a first portion positioned between a second portion and a third portion, the second portion positioned between the first portion and an outlet of the thrust recovery outflow valve, the first portion including a curved profile having a concave shape that transitions between the third portion and the second portion, the second portion having a tapered profile extending between a first end adjacent the first portion and a second end adjacent the outlet; wherein the first gate includes side plates extending from the first aerodynamic surface, the side plates are configured to direct the fluid in the fluid flow passageway toward the outlet, wherein said side plates are further configured to prevent the fluid from exiting sides of said outflow valve and direct the fluid generally aft of said outflow valve; and a frame adapted to allow mounting or coupling of said thrust recovery outflow valve to said aircraft, wherein in use, said outlet of said outflow valve is positioned adjacent to an outer surface of said aircraft and said first aerodynamic surface and said second aerodynamic surface enable a thrust recovery vector exiting the outlet to be substantially parallel relative to a direction of flight of the aircraft. a first gate having a first aerodynamic surface and a second gate having a second aerodynamic surface, the first gate to move relative to the second gate between an open position to allow fluid flow to atmosphere and a closed position to prevent fluid flow to atmosphere, the first aerodynamic surface of the first gate being spaced from the second aerodynamic surface of the second gate to define a fluid flow passageway having a convergent-divergent shape or profile when the thrust recovery outflow valve is in the open position, the first aerodynamic surface having a first portion positioned between a second portion and a third portion, the second portion positioned between the first portion and an outlet of the thrust recovery outflow valve, the first portion including a curved profile having a concave shape that transitions between the third portion and the second portion, the second portion having a tapered profile extending between a first end adjacent the first portion and a second end adjacent the outlet; wherein the first gate includes side plates extending from the first aerodynamic surface, the side plates are configured to direct the fluid in the fluid flow passageway toward the outlet, wherein said side plates are further configured to prevent the fluid from exiting sides of said outflow valve and direct the fluid generally aft of said outflow valve; and a frame adapted to allow mounting or coupling of said thrust recovery outflow valve to said aircraft, wherein in use, said outlet of said outflow valve is positioned adjacent to an outer surface of said aircraft and said first aerodynamic surface and said second aerodynamic surface enable a thrust recovery vector exiting the outlet to be substantially parallel relative to a direction of flight of the aircraft.