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 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 , wherein the spin axis of each of said right side wing rotors is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly , said left side wing assembly comprising: a plurality of left side wing rotors 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 , wherein the spin axis of each of said left side wing rotors 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 in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle , and wherein a most inboard rotor of said plurality of left side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle . a main vehicle body ; a right side wing assembly , said right side wing assembly comprising: a plurality of right side wing rotors 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 , wherein the spin axis of each of said right side wing rotors is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly , said left side wing assembly comprising: a plurality of left side wing rotors 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 , wherein the spin axis of each of said left side wing rotors 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 in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle , and wherein a most inboard rotor of said plurality of left side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle . a plurality of right side wing rotors 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 , wherein the spin axis of each of said right side wing rotors is tilted forward in the range of 5-20 degrees, wherein the tilt angle is not adjustable; a left side wing assembly , said left side wing assembly comprising: a plurality of left side wing rotors 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 , wherein the spin axis of each of said left side wing rotors 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 in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle , and wherein a most inboard rotor of said plurality of left side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle . <EOS>