3. (40 points) Peter, an aerospace engineer, proposed the wing planform as shown by the figure below below Cr = 24.0'. C

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3 40 Points Peter An Aerospace Engineer Proposed The Wing Planform As Shown By The Figure Below Below Cr 24 0 C 1 (89.01 KiB) Viewed 15 times

3. (40 points) Peter, an aerospace engineer, proposed the wing planform as shown by the figure below below Cr = 24.0'. Ct = 6.0', the span b=160', the inner edge of flap yi=9.6', the outer edge of flap yo=56.0' under the given conditions: the clean maximum lift coefficient Clmax = 1.4, the maximum lift coefficient for take-off, Clmasto = 2.8, the sweep angle A =35°, a Fowler flap with the ratio of flap chord length C+C =0.30, and the deflection angle of = 40°. Peter is not sure if the flap configuration can satisfy the requirements for take-off for the airplane with the fuselage diameter of 19.2 у C Right wing Fowler flap on right wing with C+C =0.30 9.60 Ct y=56.0 (a) What is the ratio of flapped wing area over wing area S. SwfS which Peter proposed (b) Determine the minimum required value of the required incremental section lift coefficient change, AC, based on the conditions Peter proposed. (e) Determine the incremental section lift coefficient change that the Fowler flap, with the ratio of flap chord length C+C =0.30 and the deflection angle of = 40°, can actually generate. (d) How will you change the flap configuration, yo, if you feel that yo=56 ft Peter proposed is not long enough based on your answers above.