Consider a CP-1 airplane. The characteristics of the airplane are as follows: wingspan = 35.8 ft, wing area = 174 ft, normal gross weight =2950 lb, fuel capacity: 65 gal of aviation gasoline, the parasite drag coefficient CD,0=0.025, Oswald efficiency factor = 0.8, the propeller efficiency = 0.8. The power plant comprises one-piston engine of 230 hp at sea level. Analytically calculate the maximum rate of climb for the CP-1 at 18000 ft. Refer to the table below for standard values. picture The maximum rate of climb for the CP-1 at 18000 ft is ft/min. hG, ft h, ft Temperature T, R Pressure p, lb/ft Density 0, slugs/ft 6,000 5,998 497.30 1.6960 +3 1.9869-3 7,000 6,998 493.73 1.6331 1.9270 8,000 7.997 490.17 1.5721 1.8685 9,000 8,996 486.61 1.5129 1.8113 9,500 9,496 484.82 1.4840 1.7833 10,000 9,995 483.04 1.4556 1.7556 10,500 10,495 481.26 1.4276 1.7282 11,000 10,994 479.48 1.4000 1.7011 11,500 11,494 477.70 1.3729 1.6744 12,000 11,993 475.92 1.3462 1.6480 12,500 12,493 474.14 1.3200 1.6219 13.000 12.992 472.36 1.2941 1.5961 13,500 13,491 470.58 1.2687 +3 1.5707-3 14,000 13,991 468.80 1.2436 1.5455 14,500 14,490 467.01 1.2190 1.5207 15,000 14,989 465.23 1.1948 1.4962 15,500 15,488 463.45 1.1709 1.4719 16,000 15,988 461.67 1.1475 1.4480 16,500 16,487 459.89 1.1244 1.4244 17,000 16,986 458.11 1.1017 1.4011 17,500 17,485 456.33 1.0794 1.3781 18,000 17,984 454.55 1.0575 1.3553 22,000 21,977 440.32 8.9459 1.1836 22,500 22,476 438.54 8.7576 1.1634 23,000 22,975 436.76 8.5724 1.1435 23,500 23,474 434.98 8.3905 + 2 1.1238-3 24,000 23,972 433.20 8.2116 1.1043