aub =0.08. The area and chord of the wing are 0.1m and 0.1 m, respectively. Now...

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aub =0.08. The area and chord of the wing are 0.1m and 0.1 m, respectively. Now assume that a horizontal tail is added to this model. We have the flowing parameters: =0.17m, S = 0.02m, i, = 2.5, a=0.1 per degree, &=0 and e/a=0.4. (a) (10pts) If the angle of attack = 9.38 (ZLL), calculate C for the airplane model. M (b) (5pts) Does this model has longitudinal static stability and balance? (c) (5pts) Calculate the neutral point location. aub =0.08. The area and chord of the wing are 0.1m and 0.1 m, respectively. Now assume that a horizontal tail is added to this model. We have the flowing parameters: =0.17m, S = 0.02m, i, = 2.5, a=0.1 per degree, &=0 and e/a=0.4. (a) (10pts) If the angle of attack = 9.38 (ZLL), calculate C for the airplane model. M (b) (5pts) Does this model has longitudinal static stability and balance? (c) (5pts) Calculate the neutral point location.