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) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said right side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly (103, 203), said left side wing assembly (103, 203) comprising: a plurality of left side wing rotors (104, 204) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said left side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable, wherein a most inboard rotor of said plurality of right side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200), and wherein a most inboard rotor of said plurality of left side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200). 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) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said right side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly (103, 203), said left side wing assembly (103, 203) comprising: a plurality of left side wing rotors (104, 204) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said left side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable, wherein a most inboard rotor of said plurality of right side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200), and wherein a most inboard rotor of said plurality of left side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200). a plurality of right side wing rotors (104, 204) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said right side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly (103, 203), said left side wing assembly (103, 203) comprising: a plurality of left side wing rotors (104, 204) in a forward swept configuration along a linear line or along a curving line, the rotors staggered along the longitudinal axis of the aerial vehicle (100, 200), wherein the spin axis of each of said left side wing rotors (104, 204) is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable, wherein a most inboard rotor of said plurality of right side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200), and wherein a most inboard rotor of said plurality of left side wing rotors (104, 204) in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle (100, 200).