The following data were taken from a flight test of a PA-32R-300 Cherokee-6 aeroplane. Altitude (n)...

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The following data were taken from a flight test of a PA-32R-300 Cherokee-6 aeroplane. Altitude (n) 4540 4560 4700 4580 5320 4620 4740 4900 4880 4820 4880 4740 (km) 1.384 1.390 1.396 1.622 1.408 1.445 1.494 1.487 1.469 1.487 1.445 (mph) (m/s) 91.0 40.7 48.7 56.3 69.3 39.8 46.9 55.0 67.5 38.9 46.0 54.5 68.0 109 126 155 89.0 105 123 151 87.0 103 122 152 Mass (slugs) 113.4 113.0 112.9 112.7 100.4 100.2 100.0 99.84 88.51 88.35 88.20 88.04 (kg) 1656 1650 1649 1646 1466 1463 1461 1458 1293 1290 1288 1286 į, (deg) (in) 93.89 93.89 93.89 1.5 0 -1.0 -2.0 93.89 4.5 86.82 20 86.82 0.3 86.82 -1.0 86.82 7.2 80.43 3.5 80.43 1.5 80.43 0 80.43 Acc (cm) 238.5 238.5 238.5 238.5 220.5 220.5 220.5 220.5 204.3 204.3 204.3 204.3 The data were taken in trimmed level flight. xco is the distance of the CG aft of the nose of the aircraft. The aircraft has an all-moving tail and thus it is used instead of 8., to trim the aircraft. The wing area is S = 16.21 m². a) Plot tail-setting angle, i, versus the lift coefficient of the aircraft for each of the three CG locations. [9 Marks] b) Curve fit the data points in (a) with three straight lines having a common intercept. [6 Marks] c) Use a graphical technique to find the location of the neutral point (controls fixed), relative to the nose of the aircraft [6 marks] d) Explain the key features of the dutch roll dynamic mode of an aircraft. [4 marks] The following data were taken from a flight test of a PA-32R-300 Cherokee-6 aeroplane. Altitude (n) 4540 4560 4700 4580 5320 4620 4740 4900 4880 4820 4880 4740 (km) 1.384 1.390 1.396 1.622 1.408 1.445 1.494 1.487 1.469 1.487 1.445 (mph) (m/s) 91.0 40.7 48.7 56.3 69.3 39.8 46.9 55.0 67.5 38.9 46.0 54.5 68.0 109 126 155 89.0 105 123 151 87.0 103 122 152 Mass (slugs) 113.4 113.0 112.9 112.7 100.4 100.2 100.0 99.84 88.51 88.35 88.20 88.04 (kg) 1656 1650 1649 1646 1466 1463 1461 1458 1293 1290 1288 1286 į, (deg) (in) 93.89 93.89 93.89 1.5 0 -1.0 -2.0 93.89 4.5 86.82 20 86.82 0.3 86.82 -1.0 86.82 7.2 80.43 3.5 80.43 1.5 80.43 0 80.43 Acc (cm) 238.5 238.5 238.5 238.5 220.5 220.5 220.5 220.5 204.3 204.3 204.3 204.3 The data were taken in trimmed level flight. xco is the distance of the CG aft of the nose of the aircraft. The aircraft has an all-moving tail and thus it is used instead of 8., to trim the aircraft. The wing area is S = 16.21 m². a) Plot tail-setting angle, i, versus the lift coefficient of the aircraft for each of the three CG locations. [9 Marks] b) Curve fit the data points in (a) with three straight lines having a common intercept. [6 Marks] c) Use a graphical technique to find the location of the neutral point (controls fixed), relative to the nose of the aircraft [6 marks] d) Explain the key features of the dutch roll dynamic mode of an aircraft. [4 marks]

Answer rating: 100% (QA)

a Plot of tailsetting angle delta vs lift coefficient CL for each CG location A graph is plotted wit... View the full answer