Rotor design changes intended to improve tiltrotor whirl-flutter stability margins were analyzed. A baseline analytical model of the XV-15 was established, and then a thinner, composite wing was designed to be representative of a high-speed tiltrotor. The rotor blade design was modified to increase the stability speed margin for the thin-wing design. Small rearward offsets of the aerodynamic-center locus with respect to the blade elastic axis created large increases in the stability boundary. The effect was strongest for offsets at the outboard part of the blade, where an offset of the aerodynamic center by 10% of tip chord improved the stability margin by over 100 knots. Forward offsets of the blade center of gravity had similar but less pronounced effects. Equivalent results were seen for swept-tip blades. Appropriate combinations of sweep and pitch stiffness completely eliminated whirl flutter within the speed range examined; alternatively, they allowed large increases in pitch-flap coupling (delta-three) for a given stability margin. A limited investigation of the rotor loads in helicopter and airplane configuration showed only minor increases in loads. Acree, C. W., Jr. and Peyran, R. J. and Johnson, Wayne Ames Research Center NASA/TP-2004-212262, AFDD/TR-04-001, A-0309307 FLUTTER; ROTOR AERODYNAMICS; XV-15 AIRCRAFT; MATHEMATICAL MODELS; AIRCRAFT DESIGN; ROTARY STABILITY; TILT ROTOR AIRCRAFT; THIN WINGS; AEROELASTICITY; FLAPPING; AERODYNAMIC BALANCE; LOADS (FORCES); STIFFNESS; HIGH SPEED