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Exercise 3: Lift and Airfoils
Purpose
Evaluate the relationships between Coefficient of Lift (CL) and Angle of Attack (AOA), Airfoil
Camber, and Airfoil Thickness and the variables of the Lift Equation using graphs and
equations. If you are ab

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Exercise 1: Rectilinear Motion
Uniformly Accelerated Rectilinear Motion and Newtons Law of Momentum
Equations to use (remember to keep track of units):
F = ma
T-D-f = ma
VF = VI + a t
KE = mV2
HP= T*V kts /325
1 kt = 1.69 ft/sec
m = W/g
VF 2 = VI 2 + 2

Keith Church Mod 2.6
Exercise 2: Airspeed Determination
Givens:
Altitude: FL310 (31,000 ft Pressure Altitude)
Indicated Airspeed: 250 KIAS
Indicated Outside Air Temperature (IOAT) or Total Temperature: -30 deg C
Figure 2.1 for Atmosphere
Figure 3.1 Positi

6.4 Aircraft performance
Refer to Figure 6.11 in Flight Theory and Aerodynamics (Doyle & Lewis, 1965) and assume Weight =
15,000 lb.
1. Find Climb Angle at 300 KTAS at 100 % RPM
Ta Tr
Ta 4250 Tr 1000 W=15,000lb
W
4250 1000
sin
.21666sin = 12.51 degrees

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This document was developed for online use in ASCI 310. File Name: Exercise_1 Updated: 11June12
Exercise 1: Rectilinear Motion
Background
The average accelerations of a US Navy fighter jet takeoff to an US Air Force fighter jet takeoff
are very differen

1
Exercise 1: Rectilinear Motion
Uniformly Accelerated Rectilinear Motion and Newtons Law of Momentum
Equations to use (remember to keep track of units):
F = ma
T-D-f = ma
VF = VI + a t
KE = mV2
HP= T*V kts /325
1 kt = 1.69 ft/sec
m = W/g
VF 2 = VI 2 + 2

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Exercise 2: Standard Atmosphere Airspeed
Givens:
Indicated Altitude(IA)
= 10,500 ft.
Baro-altimeter Setting
= 30.42 in. Hg
Temperature
= Standard atmosphere minus 10o F (ISA -10F)
Indicated airspeed
= 300 KIAS
Standard Atmosphere
= Flight Theo