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.