An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS = 242.4 kts. Find the aircraft's AOA for steady. CL 1.6- 1.4- 1.2- 1.0 0.8 0.6 0.4 0.2 0 L 02 ---Straight portion Clux J 1 4 6 8 10 12 14 16 18 Angle of attack (a) Eigure 4.12 C vs. AOA for a symmetrical airfoil. Stall angle of attack

An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS = 242.4 kts. Find the aircraft's AOA for steady. CL 1.6- 1.4- 1.2- 1.0 0.8 0.6 0.4 0.2 0 L 02 ---Straight portion Clux J 1 4 6 8 10 12 14 16 18 Angle of attack (a) Eigure 4.12 C vs. AOA for a symmetrical airfoil. Stall angle of attack

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Concept explainers

Moment of Inertia

Inertia can be termed as a resistance offered by a body to change its state. A rigid body initially at rest will apply resistance when acted by an external force that tends to change its state of rest or velocity, or a body initially at motion will provide resistance in changing its state of velocity or motion for coming to a state of rest. In other words, Newton's first law of motion describes the law of inertia of a rigid body.

Question

An aircraft has the CL-a curve shown in Figure 4.12.
The following
data applies:
Weight = 20 000 lb
Wing area, S = 340 sq. ft.
Density altitude = 10 000 ft
TAS 242.4 kts.
Find the aircraft's AOA for steady.
CL
1.6-
1.4-
1.2-
1.0
0.8
0.6
0.4
0.2
0
L
02
----Straight portion
Clux
J 1
4 6 8 10 12 14 16 18
Angle of attack (a)
Eigure 4.12 C vs. AOA for a symmetrical airfoil.
Stall angle
of attack

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