Reference the P_r curve that is shown for a propeller airplane in Figure 7.24. Find the angle of climb at 125 KTAS given the following information: Weight=20000lbs. P_a=3500 HP

2000+ 1500 1000 500 = 4000 DV 325 Horsepower required: 3000 2000 1000 Prop Airplane data Weight 20 000 lb Wing area (S) 500 ft Sea level density o = 1 Max endurance FF min HP, min DV min r Max endurance 3/ 3/2 CL CD max Horsepower required (HP)