1. Find Climb Angle at 250 KTAS at 100 % RPM

2. Find Rate of Climb at 300 KTAS at 100 % RPM.

3. Find Max Level Airspeed at 95% RPM.

4. Find Max Range Airspeed (VBR) and Max Endurance Airspeed (VBE).

Propeller Aircraft Performance

Refer to Figure 8.4 in Flight Theory and Aerodynamicsand assume:

· W = 20,000 lb

· S = 500 ft²

· Density Sea Level Standard Day

5. Find Max Specific Range and Max Range Airspeed (KTAS).

6. Find Max Specific Endurance and Max Endurance Airspeed (KTAS).

7. Find Max Rate of Climb and Max Rate of Climb Airspeed.

8. Find new Max Range Airspeed after fuel has burned down and W = 15,000 lb.

Landing Performance

W = 15,000 lbCLMax = 1.5

S = 500 ft2Thrust@ Idle = 500 lb

75% of Weight on Main Tires 25 % of Weight on Nose Tire

Average Drag = 500 lbSea level standard day

9. Find Approach Speed if Vapproach = 1.2 * Vstall (KTAS) (For landing and takeoff performance use KTAS.At sea level standard day KEAS=KTAS).

10. Find Average Rolling Friction (lb) on Nose Tire during Landing Rollout if Rolling Coefficient of Friction = 0.2.

11. Find Average Braking Friction (lb) on Main Tires during Landing Rollout on Dry Concrete. Use Figure 13.9.

12. Find Average Deceleration (ft/s2) during landing rollout.Assume Lift on wing is zero during landing rollout.Account for residual Thrust, Rolling Friction, Drag, and Braking Friction.

13. Find Landing Distance Ground Roll-out (ft)

14. Find Landing Distance (ft) if Runway is at 5,000 ft Density Altitude.