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 . <EOS>