Reference no: EM13748735

1. Given conditions of "Saw-tooth" climb flight test.

Pressure Altitude-2000 ft                Weight 300,000 lbs

Single engine                                Method Constant Airspeed Climb +/- 500 ft

Temperature:Standard                    (Climb from 1500 ft to 2500 ft)

                                                 Assume negligible airspeed errors due to position and compressibility

Airspeed	Airspeed	Climb Time	Average Rate of Climb	Average Rate of Climb	Angle of Climb
(KIAS)	(KTAS)	(s)	(ft/min)	(kts)	(deg)
140		80
160		65
180		60
190		70

Fill out the above table.

Find: (a) Indicated Airspeed for Vx(Best Angle Climb Airspeed) and Vy(Best Rate of Climb Airspeed)

(b) Angle of Climb for Vx

(c) Rate of Climb for Vy

(d) Specific Excess Power at Vy

(e) Excess Thrust at Vy and Vx

2. Follow on from Exercise 4:

Given Conditions:

            Gross Weight for Cruise = 300,000 lbs

            Wing Area = 3050 ft²

            Wing Span = 156 ft

            Wing Efficiency = .80

            C_Dp = 0.0119

            Twin turbofan engine Aircraft

            Thrust @ sea level = 50,000 lb/per engine

            Temp-Standard

Figure 2.1

Figure 4.3, 4.5

Figure 5.1

Figure 6.5

(a) Find Rate of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).

(b) Find Angle of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).

3. Find Cost Index (lb/hr) of an aircraft that has operating costs including maintenance and aircrew of $ 3,000 /hr with fuel costs of $5.00 / gallon.

Assume Jet Fuel = 6.8lb/gallon.

Generic Jet Transport Low and High Speed Lift Curves

Figure 4.5: Generic Transport Jet Low Speed Drag Polar (Flaps Up an Gear Up)

Figure 5.1: Generic Transport Jet Drag or Thrust Required (Weight = 300,000 p)