A design optimization procedure for high-speed prop-rotors

An optimization procedure has been developed to address the complex and conflicting design requirements associated with high-speed prop-rotor design. The procedure involves the couplings of aerodynamic performance and aeroelastic stability inside a closed-loop procedure. Both high-speed cruise and hover design requirements are addressed. The objective is to maximize the propulsive efficiency in axial flight while maintaining a significant figure of merit in hover. Constraints are also imposed on the aeroelastic stability in axial flight. Both structural and planform design variables are used. The optimization procedure yields significant improvements in the aerodynamic characteristics of the rotor.