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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

## 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 0.25c is located 42 feet from the nose (i.e. x 0.25 = 42 feet) The aspect ratio is 7 The taper ratio = 0.25 The sweep angle of the quarter-chord line Ac4 = 22 degrees The reference wing area S = 800 square feet From the above information, calculate and list the following: 1. The wingspan b 2. The root and tip chords Croot and Ctip 3. The mean aerodynamic chord, c 4. The y-location of the mean aerodynamic chord, Y 5. The (x,y) locations of the four corners of one of the reference wings, assuming the nose is at (0,0) 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 0 X

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Solutions Step 1 1 Wingspan b Using the aspect ratio AR formula AR b2 S where S is the reference wing area and b is the wingspan Plugging in the values AR 7 b2 800 ft2 b2 5600 ft2 b 5600 ft2 7483 ft Therefore the wingspan is approximately 7483 feet 2 Root and Tip Chords Croot and Ctip Using the taper ratio formula Ctip Croot Plugging in the value ...### Get Instant Access to Expert-Tailored Solutions

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