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Engineering · Mechanical Engineering
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speed. This effect is also evident in Fig. 227 3. It is directly proportional to wing loading. 4. It is indepnden of height for a given trve ainpeed, but decreases with height for a fixed V 5. It is directly proportional to the control-free static margin in the absence of Mach number effects, the elevator control will be heaviest at sea-level, low-speed, forward CG, and maximum weigh 2.10 Exercises 2.1 A subsoaic transport aircraft has a tapered, untwisted sweptback wing with straight The wing tips are straight and parallel to the root chord. In Appendix C and assume that the airfoil section local leading and trailing edges t the following, use the data of acrodynamic center is at the 1-chord point (a) Make an accurate three-view drawing of the wing chord plane. (b) Calculate wing aea S, aspect ratio A, taper ratio A - cc, and the mean aerody- (e) Calculate the location of the wings mean aerodynamic center, and locate it and 2 namic chord 2 on the side view of the wing (with dimensions). (Assume a uniform additional lift coefficient CL CL (d) The aircraft is to be operated with its most rearward CG position limited to 25 t (7.62 m) aft of the apex of the wing. The distance between the wing and tail mean acrodynamic centers is 1,-55 ft (16.76 m). Estimate the tail area required to provide a control-fixed static margin of at least 0.05 at all times, Assume that a, = a. and h~ .. hw Ignore power plant effects and use aaa-0.25. Geometric Data Wing Span, b Root Chord, c Tip Chord, c 150 ft (45.72 m) 25 ft (7.62 m 12 ft (3.66 m)
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