Modified thin cambered solar panels may be used as wing sections, thereby enabling high solar panel productivity in ultralight designs to directly displace battery and fuel costs. Computational studies were performed to better understand limits in performance and how to achieve high lift-drag ratios (L/D). Induced thrust at leading sections of thin cambered airfoils are key to creating high L/D in 2D airfoils; however, the dynamics significantly change when loss of lift pressures across side edges of low aspect ratio (AR) designs diminish the propagation of trailing-section lift-generating sources forward. Preliminary studies on use of fences, distributed propulsion, and novel airframe designs were investigated to overcome these challenges of using thin cambered wings. Wing designs previously dismissed as having inadequate lift coefficients are now prime candidates for solar aircraft where bifacial solar modules can be greater than 2X the productivity of solar panels on Earth’s surface.