1. (50 pts) The following data is provided for the World War II Navy fighter aircraft...
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1. (50 pts) The following data is provided for the World War II Navy fighter aircraft the F6F Hellcat. The F6F has a fuselage with approximately elliptical cross sections, measurements made along the length of the fuselage at 15 different stations are provided in table 1. Figure 1 shows a side and top view of the aircraft with the station locations noted. Assume the aircraft is operating in steady level flight at its maximum speed of 381 mph at 18,000ft and weighs 12,3861b. For the purposes of this calculation assume the wing/fuselage interference factor is Qwing = 1.05, the vertical tail interference factor Qu= 1.02, the horizontal tail interference factor Qht = 1.04. The geometry for the main wing, vertical and horizontal tails is provided in table 2. Neglect the drag for the center mounted bomb shown in figure 1. a. (40 pts) Compute the drag polar using the main components of the airplane, express your answer in the form of Cp-Cpo+KC. Plot the drag polar, ie C vs CD note that CLmax = 1.53. From the plot, estimate the maximum L/D. b. (10 pts) Compute the total drag coefficient, Cp at the operating conditions provided above. Station # 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Station (ft) 0.000 2.565 4.361 6.156 7.721 10.260 12.312 14.236 16.673 19.109 21.546 23.983 26.163 29.087 33.580 Table 1 Fuselage Data Semi-major axis, a (ft) 4.874 5.900 6.284 6.541 6.669 8.208 7.952 7.182 6.413 5.643 4.874 4.104 3.591 2.822 1.026 Semi-minor axis, b (ft) 3.591 4.874 5.130 5.130 5.002 4.874 4.745 4.361 3.848 3.591 2.822 2.309 1.796 1.026 0.641 Station #1 X=0 1 2 3 4 5 6 7 8 9 10 to Figure 1 F6F Fuselage Measurement locations 11 12 13 14 15 Table 2 Wing and Tail Data Vertical Tail Span= 5.13 ft Planform Area = 21.71 ft Wetted Area = 44.28 ft Average chord = 4.23 ft Average t/c = 0.1 Main Wing Span=43.833 ft Planform Area = 334 ft Wetted Area = 732 ft Average chord = 7.79 ft Average t/c = 0.135 Leading edge sweep = 4.7 Oswald efficiency = 0.8644 Note: the perimeter of an ellipse can be approximated using the Ramanujan approximation 37 P(a + b)(1+ 10+4-32 = Horizontal Tail Span= 18.98 ft Planform Area = 82.75 ft Wetted Area = 177.9 ft Average chord = 4.36 ft Average t/c = 0.1 a-b a+b 1. (50 pts) The following data is provided for the World War II Navy fighter aircraft the F6F Hellcat. The F6F has a fuselage with approximately elliptical cross sections, measurements made along the length of the fuselage at 15 different stations are provided in table 1. Figure 1 shows a side and top view of the aircraft with the station locations noted. Assume the aircraft is operating in steady level flight at its maximum speed of 381 mph at 18,000ft and weighs 12,3861b. For the purposes of this calculation assume the wing/fuselage interference factor is Qwing = 1.05, the vertical tail interference factor Qu= 1.02, the horizontal tail interference factor Qht = 1.04. The geometry for the main wing, vertical and horizontal tails is provided in table 2. Neglect the drag for the center mounted bomb shown in figure 1. a. (40 pts) Compute the drag polar using the main components of the airplane, express your answer in the form of Cp-Cpo+KC. Plot the drag polar, ie C vs CD note that CLmax = 1.53. From the plot, estimate the maximum L/D. b. (10 pts) Compute the total drag coefficient, Cp at the operating conditions provided above. Station # 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Station (ft) 0.000 2.565 4.361 6.156 7.721 10.260 12.312 14.236 16.673 19.109 21.546 23.983 26.163 29.087 33.580 Table 1 Fuselage Data Semi-major axis, a (ft) 4.874 5.900 6.284 6.541 6.669 8.208 7.952 7.182 6.413 5.643 4.874 4.104 3.591 2.822 1.026 Semi-minor axis, b (ft) 3.591 4.874 5.130 5.130 5.002 4.874 4.745 4.361 3.848 3.591 2.822 2.309 1.796 1.026 0.641 Station #1 X=0 1 2 3 4 5 6 7 8 9 10 to Figure 1 F6F Fuselage Measurement locations 11 12 13 14 15 Table 2 Wing and Tail Data Vertical Tail Span= 5.13 ft Planform Area = 21.71 ft Wetted Area = 44.28 ft Average chord = 4.23 ft Average t/c = 0.1 Main Wing Span=43.833 ft Planform Area = 334 ft Wetted Area = 732 ft Average chord = 7.79 ft Average t/c = 0.135 Leading edge sweep = 4.7 Oswald efficiency = 0.8644 Note: the perimeter of an ellipse can be approximated using the Ramanujan approximation 37 P(a + b)(1+ 10+4-32 = Horizontal Tail Span= 18.98 ft Planform Area = 82.75 ft Wetted Area = 177.9 ft Average chord = 4.36 ft Average t/c = 0.1 a-b a+b
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College Accounting A Practical Approach
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11th Canadian Edition
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