An aerial vehicle navigation method, comprising: receiving a command to navigate in a direction that includes a horizontal component; determining that the aerial vehicle is in a vertical takeoff and landing (VTOL) orientation such that: a fuselage of the aerial vehicle is at an angle with respect to a vertical orientation; a ring wing of the aerial vehicle is aligned in a first plane that is substantially horizontal; and a plurality of propulsion mechanisms of the aerial vehicle are provided, wherein adjacent propulsion mechanisms are angled toward one another to form pairs of propulsion mechanisms allowing horizontal forces from each propulsion mechanism to cancel out such that the pair of propulsion mechanisms can produce a vertical force; generating a first force by a first propulsion mechanism of the plurality of propulsion mechanisms that cause a pitch of the aerial vehicle to increase such that the aerial vehicle pitches forward and rotates from a VTOL orientation to a horizontal flight orientation such that: the fuselage of the aerial vehicle is in a horizontal orientation in a direction of travel of the aerial vehicle; the ring wing is offset such that a lower segment of the ring wing is in a leading wing position and an upper segment of the ring wing is in a rear wing position; a second propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a second force in a substantially horizontal direction; and a third propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a third force in the substantially horizontal direction; generating the second force and the third force from the second propulsion mechanism and the third propulsion mechanism to cause the aerial vehicle to surge in a horizontal direction while the aerial vehicle is in the horizontal flight orientation; and wherein the ring wing of the aerial vehicle produces a lift sufficient to maintain the aerial vehicle at an altitude when the aerial vehicle is in the horizontal flight orientation and surging in the horizontal direction. receiving a command to navigate in a direction that includes a horizontal component; determining that the aerial vehicle is in a vertical takeoff and landing (VTOL) orientation such that: a fuselage of the aerial vehicle is at an angle with respect to a vertical orientation; a ring wing of the aerial vehicle is aligned in a first plane that is substantially horizontal; and a plurality of propulsion mechanisms of the aerial vehicle are provided, wherein adjacent propulsion mechanisms are angled toward one another to form pairs of propulsion mechanisms allowing horizontal forces from each propulsion mechanism to cancel out such that the pair of propulsion mechanisms can produce a vertical force; a fuselage of the aerial vehicle is at an angle with respect to a vertical orientation; a ring wing of the aerial vehicle is aligned in a first plane that is substantially horizontal; and a plurality of propulsion mechanisms of the aerial vehicle are provided, wherein adjacent propulsion mechanisms are angled toward one another to form pairs of propulsion mechanisms allowing horizontal forces from each propulsion mechanism to cancel out such that the pair of propulsion mechanisms can produce a vertical force; generating a first force by a first propulsion mechanism of the plurality of propulsion mechanisms that cause a pitch of the aerial vehicle to increase such that the aerial vehicle pitches forward and rotates from a VTOL orientation to a horizontal flight orientation such that: the fuselage of the aerial vehicle is in a horizontal orientation in a direction of travel of the aerial vehicle; the ring wing is offset such that a lower segment of the ring wing is in a leading wing position and an upper segment of the ring wing is in a rear wing position; a second propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a second force in a substantially horizontal direction; and a third propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a third force in the substantially horizontal direction; the fuselage of the aerial vehicle is in a horizontal orientation in a direction of travel of the aerial vehicle; the ring wing is offset such that a lower segment of the ring wing is in a leading wing position and an upper segment of the ring wing is in a rear wing position; a second propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a second force in a substantially horizontal direction; and a third propulsion mechanism of the plurality of propulsion mechanisms is oriented substantially horizontally to produce a third force in the substantially horizontal direction; generating the second force and the third force from the second propulsion mechanism and the third propulsion mechanism to cause the aerial vehicle to surge in a horizontal direction while the aerial vehicle is in the horizontal flight orientation; and wherein the ring wing of the aerial vehicle produces a lift sufficient to maintain the aerial vehicle at an altitude when the aerial vehicle is in the horizontal flight orientation and surging in the horizontal direction.