Airplane specifications are given follows: Amax fuselage, cross-section = 38 ft², V I body reduced 28 ft 3 Wing sweep angle, A=15"," Wing area, S650 ft² / V Airplane weight, W=130,000 lb/ Subsonic Drag Polar: Co-0.013+0.075CL² V Divergence Mach number, Moo = 0.9✓ Altitude data at altitude of 5,000 ft: P5.000 2.0482x10 slugs/ft', as soon 1097 ft/s Empirical drag efficiency factor, EwD= 1.6. C 0.00 006 00 0.04 aas 0.00 Max. Available Thrust: (TA)max = 26x10³ lb (Assumed constant with velocity) 00 • a 02 04 06 08 1.0 1.2 Assuming airplane flying at 5000 ft find the following: 1. The maximum velocity considering the drag-divergence using Raymer's procedure 2. The maximum rate of climb and 3. The max angle of climb. ground. 0.08 Zero-lift drag coefficient Coo 0.07 0.06 0.05 L 1 0.04- 0.03 C 0.02 E 0.002 0.01 L 0 0.2 0.4 0.6 0.8 1.0 110 M 1.2