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Suppose a jet's fuselage measures 80 feet long and 7 feet in diameter. Our objective is to design a reference wing for it using the following parameters: The subsonic aerodynamic center at 0.25 is located 42 feet from the nose (i.e. Xy 25z = 42 feet) The aspect ratio is 7 The taper ratioA =0.25 The sweep angle of the quarter-chord line Ajy = 22 degrees The reference wing area S = 800 square feet From the above information, calculate and list the following: The wingspan b The root and tip chords Cioot and Cyp The mean aerodynamic chord, The y-location of the mean aerodynamic chord, The (x,y) locations of the four corners of one of the reference wings, assuming the nose is at (0,0) U L0 ) Draw a scale diagram of one of the reference wings and mean aerodynamic chords with respect to the fuselage centerline, similar to the drawing below. Do not worry about drawing the tail or aft body, or the precision of the nose geometry. y