A high school project involves building a model ultralight airplane. Some of the stu- dents propose making an airfoil from a sheet of plastic 1.5 m long by 2 m wide at an angle of attack of 12o. At this airfoil's aspect ratio and angle of attack the lift and drag coefficients are CL=0.72 and CD=0.17. If the airplane is designed to fly at 12 m/s, what is the maximum total payload? What will be the required power to maintain flight? Does this proposal seem feasible?