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