An aerial vehicle (100, 200) adapted for vertical takeoff and horizontal flight using rotors to simulate traditional wing aerodynamics, said aerial vehicle (100, 200) comprising: a main vehicle body (101, 201); a right side wing assembly (102, 202), said right side wing assembly (102, 202) comprising: a plurality of right side wing rotors (104, 204) along a first span direction, wherein the spin axis of said right side wing rotors (104, 204) is tilted forward; and a right side trailing edge wing (108, 208), said right side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of right side wing rotors (104, 204); and a left side wing assembly (103, 203), said left side simulated wing (103, 203) comprising: a plurality of left side wing rotors (104, 204) along a span direction, wherein the spin axis of said left side wing rotors (104, 204) is tilted forward; and a left side trailing edge wing (108, 208), said left side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of left side wing rotor (104, 204), wherein the spin axis of said right side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees; and wherein said aerial vehicle (100, 200) does not have controllable control surfaces. a main vehicle body (101, 201); a right side wing assembly (102, 202), said right side wing assembly (102, 202) comprising: a plurality of right side wing rotors (104, 204) along a first span direction, wherein the spin axis of said right side wing rotors (104, 204) is tilted forward; and a right side trailing edge wing (108, 208), said right side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of right side wing rotors (104, 204); and a plurality of right side wing rotors (104, 204) along a first span direction, wherein the spin axis of said right side wing rotors (104, 204) is tilted forward; and a right side trailing edge wing (108, 208), said right side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of right side wing rotors (104, 204); and a left side wing assembly (103, 203), said left side simulated wing (103, 203) comprising: a plurality of left side wing rotors (104, 204) along a span direction, wherein the spin axis of said left side wing rotors (104, 204) is tilted forward; and a left side trailing edge wing (108, 208), said left side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of left side wing rotor (104, 204), wherein the spin axis of said right side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees; and wherein said aerial vehicle (100, 200) does not have controllable control surfaces. a plurality of left side wing rotors (104, 204) along a span direction, wherein the spin axis of said left side wing rotors (104, 204) is tilted forward; and a left side trailing edge wing (108, 208), said left side trailing edge wing (108, 208) having a first end at said main vehicle body (101, 201) and moving outboard along the first span direction rearward of the plurality of left side wing rotor (104, 204), wherein the spin axis of said right side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotors (104, 204) is tilted forward relative to vertical at an angle in the range of 5-20 degrees; and wherein said aerial vehicle (100, 200) does not have controllable control surfaces.