Based upon the experimental lift curve slope, compute how much the aircraft weighs if it flies in steady, level flight at 300 ft/s and wing has a geometric angle of attack of 4 given: Chord = 2ft, span = 40ft, span efficiency = 0.9, i calculated the lift curve slope to be 5.42 from using the equation a = a0/1+57.3(a0)/pi*AR*e), I used 2*pi for a0, i need an answer with every step i will throw alot of points at this question.