used to tune the spanwise lift distribution of the aircraft in forward flight for maximum efficiency check stability predictions of lower fidelity analyses and estimate rotor efficiency and download caused by the wing a cfd result for a 55 pound prototype at 43 knot cruise at standard sea level conditions is shown in fig1 showing the complex tip vortex system that develops results of this configuration show a l d in excess of 20 at this flight condition although this is expected to be somewhat reduced in the flight vehicle due to control surface gaps antennas motor cooling etc fig1 a b shows results of cfd analyses of the blade performance of a 55 pound prototype in a 100 ft min axial climb at standard sea level conditions uninstalled figure of merit computed as the ratio of ideal climb power required from momentum theory to computed power is 72 and the required thrust increment due to the download on the wing is 13 fig1 a illustrates uninstalled blades with isosurfaces of constant vorticity magnitude and with blades contoured by cp the pressure co efficient non dimensionalized by the local rotational velocity fig1 b illustrates the blades and the wing with 25 chord flaps deflected to 55 degrees showing download effects on the wing via pressure contours fig1 illustrates another embodiment of an aerial vehicle using tip rotors on both the wings and the rear elevators as evident from the above description a wide variety of embodiments may be configured from the description given herein and additional advantages and modifications will readily occur to those skilled in the.