A Combined Optimization and Inverse design Framework for Rotor Design

An approach for redesigning the tip region of helicopter rotors to achieve a desired target pressure distribution is described. In this approach, the difference between the realized target pressure distribution and the target pressure values are used to drive the changes to the blade profiles. Because the design process is independent of the analysis that generates the surface pressure distribution, this approach may be used with a variety of analyses. Sample 2-D applications on the design of low drag rotorcraft airfoil sections are presented to demonstrate the ability of the design process to change the blade section profile iteratively and rapidly. The process is subsequently applied to the S-76 rotor to explore the redesign of the rotor tip region for improved hover performance.