Exercise 5:Aircraft Performance
JetAircraft Performance (Questions 1-4)
Refer to Figure 6.11 in Flight Theory and Aerodynamics(Doyle
& Lewis, 1965) and assume Weight = 12,000 lb.
1.Find Climb Angle at 250 KTAS at 100 % RPM
2.Find
Rate of Climb at 300 KTAS at 100 % RPM.
2.Find
Max Level Airspeed at 95% RPM.
4.Find Max Range Airspeed (VBR) and
Max Endurance Airspeed (VBE).
Propeller
Aircraft Performance (Questions 5-8)
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 (Questions 9-14)
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.