A method is described for solving the minimum-induced loss (MIL) rotor design problem. First, the generalized Betz condition for MIL rotors is developed. Because the resulting lift distributions would generally exceed the maximum blade lift coefficient on the retreating side of the rotor, the necessary conditions are extended to include constraints on the lift. A method for solving for the optimum lift distribution using finite elements is described. Numerical results are presented for a typical rotor in forward flight. The MIL rotor may have on the order of 10% less induced power loss than a typical unoptimized rotor. © 1994 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.