For the TAA class of aircraft, the wing produces approximately 25% of the total aircraft drag. Laminar flow airfoil and wing technology offered the potential to significantly lower this value. More recent laminar flow airfoil development has produced airfoils capable of attaining laminar flow over 70% of the wing’s chord. However, these airfoils suffered from high pitching moment and associated high trim drag. In addition to these maladies, older laminar flow airfoils also suffered from severe loss of lift when the surface became contaminated and lost laminar flow [