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16.00 Introduction to Aerospace and Design
Problem Set #3
AIRCRAFT PERFORMANCE FLIGHT SIMULATION LAB
Solution
I collected flight data at 10 different conditions, and also flew from 10,000 ft to 9,000 ft to get
more time to fly stably and more accurately measure vertical speed.
Data are shown in the table below.
Indicated airspeed computed directly from the airspeed indicator and converted to ft/s
True airspeed = 1.154 x (indicated airspeed) as per Problem Set #3 handout
Vertical speed computed from the Flight Analysis tool, converted to ft/s
h
&
Flight path angle computed from
γ
= sin
−1
v
Lift computed from L = W cos(γ)
L/D computed from L/D = cot(γ)
L
CL computed from CL =
2
1
ρ
v 2 S
D
CD computed from CD = CL L
Flight indicated true vertical flight path
Condition airspeed (ft/s) airspeed (ft/s) speed (ft/s) angle (deg) Lift (N) L/D Cl Cd
72.62 83.81 2.31 1.58 849.68 36.30 0.76 0.02
79.38 91.60 2.45 1.53 849.70 37.34 0.63 0.02
87.82 101.35 2.78 1.57 849.68 36.48 0.52 0.01
96.27 111.09 3.19 1.65 849.65 34.76 0.43 0.01
103.02 118.89 3.73 1.80 849.58 31.89 0.38 0.01
113.16 130.58 4.61 2.02 849.47 28.29 0.31 0.01
131.73 152.02 6.54 2.47 849.21 23.21 0.23 0.01
148.62 171.51 9.35 3.12 848.74 18.32 0.18 0.01
172.27 198.80 14.17 4.09 847.84 14.00 0.13 0.01
209.42 241.67 25.24 6.00 845.35 9.52 0.09 0.01
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