1. Fig. 9 plots the ratio of total lift (force in vertical direction perpendicular to the flight velocity and span) to rigid lift. The drastic loss of effective vertical lifl is clearly observed as compared to linear results. The main significance of this result lies in the fact LhaL, if stall angle is around 120022, then the rigid-wing analysis gives the stall speed to be 20 m/s, whereas t,hc aclud flexible aircraft would stall even at much higher flighL speed of around 25 m/s. This would mean rcductiou iu the actual flight envelope.
2. This work was supported by the U.S. Air Force Office of Scientific Research (Grant number F49620-98- l-0032), the technical monitor of which is Maj. Brian P. Sanders, Ph.D. The Daedalus model data provided by Prof. Mark Drela (MIT) is gratefully acknowledged.
3. Nonlinear aeroelastic analysis of aircraft with high-aspect-ratio wings