Altitude ho, m h, m Temperature T, K 7,000 6,992 242.71 7,100 7,092 242.06 Pressure p, N/m 4.1105+4 4.0531 Density 6, kg/m 5.9002-1 5.8334 7,200 7,192 241.41 3.9963 5.7671 7,300 7,292 240.76 3.9402 5.7015 7,400 7,391 240.12 3.8848 5.6364 7,500 7,491 239.47 3.8299 5.5719 7,600 7,591 238.82 3.7757 5.5080 7,700 7,691 238.17 3.7222 5.4446 7,800 7,790 237.52 3.6692 5.3818 7,900 7,890 236.87 3.6169 5.3195 8,000 7,990 236.23 3.5651 +4 5.2578-1 8,100 8,090 235.58 3.5140 5.1967 8,200 8,189 234.93 3.4635 5.1361 8,300 8,289 234.28 3.4135 5.0760 8,400 8,389 233.63 3.3642 5.0165 8,500 8,489 232.98 3.3154 4.9575 8,600 8,588 232.34 3.2672 4.8991 8,700 8,688 231.69 3.2196 4.8412 8,800 8,788 231.04 3.1725 4.7838 8,900 8,888 230.39 3.1260 4.7269 9,000 8,987 229.74 3.0800+4 9,100 9,087 229.09 3.0346 4.6706-1 4.6148 9,200 9,187 228.45 2.9898 4.5595 9,300 9,286 227.80 2.9455 4.5047 9,400 9,386 227.15 2.9017 4.4504 9,500 9,486 226.50 2.8584 4.3966 9,600 9,586 225.85 2.8157 4.3433 9,700 9.685 225.21 2.7735 4.2905 9,800 9,785 224.56 2.7318 4.2382 9,900 9,885 223.91 2.6906 4.1864 10,000 9,984 223.26 2.6500+4 10.100 10,084 222.61 2.6098 4.1351-1 4.0842 10,200 10,184 221.97 2.5701 4.0339 10,300 10.283 221.32 2.5309 3.9840 10,400 10,383 220.67 2.4922 3.9346 10,500 10,483 220.02 2.4540 3.8857 10,600 10,582 219.37 2.4163 3.8372 10,700 10,682 218.73 2.3790 3.7892 10,800 10,782 218.08 2.3422 3.7417 10,900 10,881 217.43 2.3059 3.6946 Problem 1: (10 pts) The flight test data for a given airplane at a level-flight altitude correspond to a pressure altitude of 7,000 m and a temperature altitude of 8,000 m. Calculate: a) the density of the air at the altitude, and b) the density altitude during the flight test. You are allowed to use the ISA tables in appendix A