We wish to design a swept-back wing (20 deg of sweep at the c/4 line, aspect ratio 15, span 50 ft). It is intended
to fly at a CL of 1.0 using airfoil sections with a camber of about 2%.
Find the amount of built-in twist to trim with no control surface deflections so that the static margin is 10%
and the taper ratio is chosen so that there is less than a 5% induced drag penalty due to trim (i.e. the span efficiency
is within 5% of the maximum). Also find the c.g. location and express it in feet from the root leading edge.
Draw the planform and show the location of c.g., a.c., and M.A.C..
You may use the wing analysis program in the course notes or write your own 3-d wing analysis using a discrete vortex model.