Question Statement:
Data for a light, single-engine, propeller driven aircraft in steady level flight at sea-level is as
follows: velocity V∞ = 40m/s, weight W = 13000N, lift coefficient CL = 0.65, drag coefficient CD =
0.025 + 0.04CL
2 and power available Pav = 100,000J/s. The rate of climb possible for this aircraft
under the given conditions (in m/s) is
Options:
- (A) 7.20
- (B) 5.11
- (C) 6.32
- (D) 4.23 END OF THE QUESTION PAPER AE 11/11 AE (GATE 2014) Section Q. No. Key / Range Marks Section Q. No. Key / Range Marks GA 1 A 1 AE 26 A 2 GA 2 B 1 AE 27 C 2 GA 3 D 1 AE 28 D 2 GA 4 C 1 AE 29 A 2 GA 5 1300 to 1300 1 AE 30 B 2 GA 6 D 2 AE 31 ‐5.01 to ‐4.99 2 GA 7 B 2 AE 32 C 2 GA 8 180 to 180 2 AE 33 1705 to 1720 2 GA 9 D 2 AE 34 B 2 GA 10 B 2 AE 35 C 2 AE 1 C 1 AE 36 C 2 AE 2 B 1 AE 37 0.99 to 1.01 2 AE 3 C 1 AE 38 0.12 to 0.13 2 AE 4 A 1 AE 39 A 2 AE 5 D 1 AE 40 B 2 AE 6 A 1 AE 41 D 2 AE 7 D 1 AE 42 D 2 AE 8 B 1 AE 43 B 2 AE 9 D 1 AE 44 D 2 AE 10 D 1 AE 45 1880 to 1881 2 AE 11 A 1 AE 46 1.10 to 1.25 2 AE 12 B 1 AE 47 74 to 76 2 AE 13 B 1 AE 48 6050 to 6250 2 AE 14 2.95 to 3.05 1 AE 49 D 2 AE 15 C 1 AE 50 C 2 AE 16 D 1 AE 51 D 2 AE 17 B 1 AE 52 18 to 20 2 AE 18 B 1 AE 53 B 2 AE 19 C 1 AE 54 C 2 AE 20 D 1 AE 55 B 2 AE 21 0.45 to 0.55 1 AE 22 D 1 AE 23 D 1 AE 24 B 1 AE 25 1.2 to 1.25 1 ‐ Aerospace Engineering