1. m = 500 slugs; 2. a = 12 fps2; 3. Drag = 282 lb, Lift = 102.6 lb; 4. Tan = 0.75, Distance = 5 mi; 5. s = 8 ft, F = 30 lb; 6. Time = 16.7 sec; 7. Takeoff roll = 1667 ft; 8. a = 5 fps2; 9. V1 = 450 fps; 10. PE = 80 × 106 ft‐lb, KE = 10 × 106 ft‐lb, TE = 90 × 106 ft‐lb; 11. HP = 5000 hp; 12.
1. c; 2. c; 3. a; 4. a; 5. d; 6. d; 7. c; 8. b; 9. a; 10. b; 11. d = 0.929, PA = 2000 ft, q = 1.078, s = 0.8618, DA = 5000 ft; 12. H = 2062.8 psf, P2 = 1931 psf, q2 = 131 psf, , , ; 13. q = 116.8 psf; 14. EAS = 337.5 knots; 15. TAS = 498 knots
1. d; 2. c; 3. d; 4. d; 5. c; 6. e; 7. d; 8. d; 9. b; 10. d
1. a; 2. c; 3. a; 4. c; 5. d; 6. d; 7. c; 8. b; 9. d; 10. a. combination, b. energy add, c. combination, d. camber chg; 11. AOA = 4°; 12. ; 13. ; 14.
1. d; 2. c; 3. d; 4. d; 5. b; 6. d; 7. d; 8. c; 9. b; 10. b; 11. ; 12. V = 172 knots; 13.
14.
V2 | (V2/V1) | Dp | (V1/V2)2 | Di | Dt |
125 | 0.530 | 270 | 1.89 | 963 | 1233 |
150 | 0.763 | 389 | 1.31 | 669 | 1058 |
172 | 1.0 | 510 | 1.0 | 510 | 1020 |
200 | 1.35 | 690 | 0.74 | 377 | 1067 |
300 | 3.04 | 1562 | 0.33 | 168 | 1720 |
400 | 5.42 | 2766 | 0.184 | 94 | 2860 |
1. d; 2. d; 3. a; 4. a; 5. a; 6. a; 7. d; 8. c; 9. c; 10. b; 11. T = 3000 lb, Efficiency = 77%; 12. , T = 4100 lb, FF0 = 6150 lb/hr; 13. ; 14. a. 500 knots, b. 240 knots, c. 0.327 (19°), d. 10,940 fpm, e. 240 knots, f. 300 knots, g. 350 knots
1. d; 2. c; 3. a; 4. b; 5. d; 6. a; 7. d; 8. c; 9. b; 10. d; 11. , ; 12. , ; 13. , SR improvement in Problem 13 = 14.154%, SR improvement in Problem 12 = 27.6%, conclusion: reduce throttle as fuel is burned; 14. SR0 = 0.2973, SR20 = 0.4108, SR improvement = 38%
1. a; 2. d; 3. c; 4. b; 5. d; 6. b; 7. b; 8. d; 9. c; 10. b; 11. 474 HP, 488 HP, 540 HP, 657 HP, 1588 HP, 3520 HP; 12. a. 340 knots, b. 0.542 (32.8°), c. 0.37 (21.7°), d. 4125 fpm, e. 4950 fpm, f. 100 knots, g. 140 knots, h. 160 knots
1. c; 2. a; 3. b; 4. c; 5. c; 6. c; 7. c; 8. b; 9. b; 10. a; 11. , ; 12. , ; 13. , Improvement = 18.7%, Improvement in Problem 12 = 53.5%; conclusion: reduce throttle as fuel is burned; 14. SR0 = SR = 0.58 nmi/lb; conclusion: no change in SR with altitude (considering airframe only)
1. d; 2. c; 3. c; 4. d; 5. a; 6. d; 7. d; 8. a; 9. a; 10. ; 11. V = 126.5 fps (75 knots); 12. S = 2576 ft; 13. S = 5796 ft; 14. S = 2087 ft; 15. S = 4025 ft
1. d; 2. b; 3. d; 4. d; 5. d; 6. a; 7. a; 8. c; 9. a; 10. a; 11. ; 12. S = 1785 ft; 13. S = 2901 ft; 14. S = 2160 ft; 15. S = 2231 ft
1. d; 2. b; 3. d; 4. b; 5. b; 6. a; 7. c; 8. c; 9. d; 10. d; 11. RC = 506.5 fpm; 12. RC = −658.5 fpm
1. b; 2. c; 3. d; 4. d; 5. d; 6. a; 7. c; 8. d; 9. d; 10. b; 11. 30.6°; 12. Verified; 13. 1.162G; 14. ROT = 3.23°/sec; 15. Verified
1. b; 2. c; 3. d; 4. c; 5. c; 6. d; 7. a; 8. c; 9. b; 10. d
1. b; 2. c; 3. a; 4. a; 5. c; 6. a; 7. c; 8. a; 9. b; 10. b
1. d; 2. b; 3. b; 4. e; 5. a; 6. h; 7. a; 8. a; 9. b; 10. d
1. c; 2. b; 3. c; 4. a; 5. d; 6. b