An aircraft propulsor comprising: a nacelle comprising a thrust reverser aperture ; a core engine circumscribed by the nacelle and comprising a plurality of fan blades configured to rotate around a first axis , wherein the nacelle and the core engine define, at least in part, a bypass flow path configured to direct airflow from the plurality of fan blades of the core engine; a thrust reverser cascade configured to be at least partially disposed within the thrust reverser aperture , comprising a plurality of straight cascade vanes coupled to the nacelle, arranged substantially orthogonal to the first axis , and configured to permit airflow from the bypass flow path through the straight cascade vanes so that the airflow exits the thrust reverser cascade substantially orthogonal to the axis , wherein the thrust reverser cascade is configured to move between a first cascade position and a second cascade position, and wherein at least the first cascade position is configured to permit airflow from the bypass flow path through the cascade vanes; a turning door disposed within the thrust reverser aperture and configured to move between at least a first turning door position and a second turning door position, wherein the turning door in the first turning door position is configured to deflect airflow from the cascade vanes to a direction with a component opposite that of airflow within the bypass flow path; and a blocker door disposed between the nacelle and the core engine and configured to move between at least a first blocker door position and a second blocker door position, wherein the blocker door in the first blocker door position blocks at least a portion of the bypass flow path, wherein the blocker door is configured to move independently of the turning door. a nacelle comprising a thrust reverser aperture ; a core engine circumscribed by the nacelle and comprising a plurality of fan blades configured to rotate around a first axis , wherein the nacelle and the core engine define, at least in part, a bypass flow path configured to direct airflow from the plurality of fan blades of the core engine; a thrust reverser cascade configured to be at least partially disposed within the thrust reverser aperture , comprising a plurality of straight cascade vanes coupled to the nacelle, arranged substantially orthogonal to the first axis , and configured to permit airflow from the bypass flow path through the straight cascade vanes so that the airflow exits the thrust reverser cascade substantially orthogonal to the axis , wherein the thrust reverser cascade is configured to move between a first cascade position and a second cascade position, and wherein at least the first cascade position is configured to permit airflow from the bypass flow path through the cascade vanes; a turning door disposed within the thrust reverser aperture and configured to move between at least a first turning door position and a second turning door position, wherein the turning door in the first turning door position is configured to deflect airflow from the cascade vanes to a direction with a component opposite that of airflow within the bypass flow path; and a blocker door disposed between the nacelle and the core engine and configured to move between at least a first blocker door position and a second blocker door position, wherein the blocker door in the first blocker door position blocks at least a portion of the bypass flow path, wherein the blocker door is configured to move independently of the turning door. <EOS>