2.8* The following data were taken from a flight test of a PA-32R-300 Cherokee-6 air- plane. Altitude VE Mass i, XCG (ft) (km) (mph) (m/s) (slugs) (kg) (deg) (in) (cm) 4540 1.384 91.0 40.7 113.4 1656 1.5 93.89 238.5 4560 1.390 109 48.7 113.0 1650 0 93.89 238.5 4700 1.433 126 56.3 112.9 1649 -1.0 93.89 238.5 4580 1.396 155 69.3 112.7 1646 -2.0 93.89 238.5 5320 1.622 89.0 39.8 100.4 1466 4.5 86.82 220.5 4620 1.408 105 46.9 100.2 1463 2.0 86.82 220.5 4740 1.445 123 55.0 100.0 1461 0.3 86.82 220.5 4900 1.494 151 67.5 99.84 1458 -1.0 86.82 220.5 4880 1.487 87.0 38.9 88.51 1293 7.2 80.43 204.3 4820 1.469 103 46.0 88.35 1290 3.5 80.43 204.3 4880 1.487 122 54.5 88.20 1288 1.5 80.43 204.3 4740 1.445 152 68.0 88.04 1286 0 80.43 204.3 The data were taken in trimmed level flight. XCG is the distance of the CG aft of the nose of the aircraft. The aircraft has an all-moving tail and thus i, is used instead of 8 to trim the aircraft. The wing area is S = 174.5 ft (16.21 m). (a) Plot tail-setting angle, i,, versus the lift coefficient of the aircraft for each of the three CG locations. (b) Curve fit the data points in (a) with three straight lines having a common inter- cept (refer to Fig. 2.18). (c) Use a graphical technique to find the location of the neutral point (controls fixed) relative to the nose of the aircraft (refer to Fig. 2.21).