A set of closed-form solutions to idealized static aeroelastic problems is presented. These solutions describe the effects of fibrous composites on flexible lifting surface divergence, lift effectiveness, and spanwise center-ofpressure location. Several examples illustrate the ability of aeroelastic tailoring to modify spanwise center-ofpressure location. Additional examples, using data generated from a matrix method of analysis, show that tailoring for forward swept wing divergence is likely to be effective out to relatively high aspect ratios and that lateral control effectiveness can be enhanced considerably by fibrous composite tailoring.