An aircraft component, made of 7075-T6 aluminum alloy, can be represented as a bar of diameter 20 mm and length of 400 mm. Calculate a) the extension of the bar under an imposed load of 80 kN, b) the load at which the bar suffers permanent deformation, and maximum load that the bar can take without fracture Table 5-2 Room-temperature properties of metallic materials Designation AM60B A1100 A7075-T6 AC41A AISI 1008 AISI 4140 AISI 304 Gray cast iron C10100 C26000 Material Composition Mg-6Al-0.3Mn Be-38Al 99.5% Al Al-5.5Zn-1.6℃u-2.5Mg Ti-6Al-4V Zn-4Al-ICU-0.04 Mg Fe-0.08C Fe-0.4C-1Cr-0.2Ni Fe-0.08C-19Cr-9Ni Fe-3C-2Si, tension Compression 99.99% Cu 70Cu-30Zn brass Ni W (at 500°C) Density, g/cm 1.8 2.1 2.71 2.8 6.6 7.87 7.82 7.9 7.15 8.9 8.53 8.9 19.3 E GPa 45 200 70 70 120 200 200 193 N.A.† 130 110 205 405 YS, MPa 130 190-310 35-150 105-500 920 160-700 420-1700 205-2000 N.A.¹ 70-365 75-450 110-620 110 TS, MPa 220 260-380 90-165 230-570 1000 330 260-700 650-1900 515-2200 150-430 570-1300 220-255 300-900 340-660 300

An aircraft component, made of 7075-T6 aluminum alloy, can be represented as a bar of diameter 20 mm and length of 400 mm. Calculate a) the extension of the bar under an imposed load of 80 kN, b) the load at which the bar suffers permanent deformation, and maximum load that the bar can take without fracture Table 5-2 Room-temperature properties of metallic materials Designation AM60B A1100 A7075-T6 AC41A AISI 1008 AISI 4140 AISI 304 Gray cast iron C10100 C26000 Material Composition Mg-6Al-0.3Mn Be-38Al 99.5% Al Al-5.5Zn-1.6℃u-2.5Mg Ti-6Al-4V Zn-4Al-ICU-0.04 Mg Fe-0.08C Fe-0.4C-1Cr-0.2Ni Fe-0.08C-19Cr-9Ni Fe-3C-2Si, tension Compression 99.99% Cu 70Cu-30Zn brass Ni W (at 500°C) Density, g/cm 1.8 2.1 2.71 2.8 6.6 7.87 7.82 7.9 7.15 8.9 8.53 8.9 19.3 E GPa 45 200 70 70 120 200 200 193 N.A.† 130 110 205 405 YS, MPa 130 190-310 35-150 105-500 920 160-700 420-1700 205-2000 N.A.¹ 70-365 75-450 110-620 110 TS, MPa 220 260-380 90-165 230-570 1000 330 260-700 650-1900 515-2200 150-430 570-1300 220-255 300-900 340-660 300

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

Thermal Properties of Materials

In mechanical engineering, the thermal property is represented as the physical quantity that is relevant to the application of heat. The thermal properties are evaluated by variations in any specific material due to low heat or high heat. The quantities that influence the thermal property of the materials are mass, density, temperature, and many others.

Question

Help with the following question

An aircraft component, made of 7075-T6 aluminum alloy, can be represented as a bar of
diameter 20 mm and length of 400 mm. Calculate a) the extension of the bar under an
imposed load of 80 kN, b) the load at which the bar suffers permanent deformation, and
maximum load that the bar can take without fracture
Table 5-2 Room-temperature properties of metallic materials
Designation
AM60B
A1100
A7075-T6
AC41A
AISI 1008
AISI 4140
AISI 304
Gray cast iron
C10100
C26000
Material
Composition
Mg-6Al-0.3Mn
Be-38Al
99.5% Al
Al-5.5Zn-1.6Cu-2.5Mg
Ti-6Al-4V
Zn-4Al-ICu-0.04 Mg
Fe-0.08C
Density,
E,
YS,
g/cm³
GPa
MPa
1.8
45
130
220
2.1
200
190-310
2.71
70
35-150
2.8
70
105-500
4.43
120
920
TH
6.6
7.87
200
160-700
7.82
200
7.9
193
7.15
N.A.
N.A.
8.9
130
70-365
8.53
110
75-450
205
405
Fe-0.4C-1Cr-0.2Ni
Fe-0.08C-19Cr-9Ni
Fe-3C-2Si, tension
Compression
99.99% Cu
70Cu-30Zn brass
Ni
W (at 500°C)
8.9
19.3
TS,
MPa
260-380
90-165
230-570
1000
330
260-700
420-1700 650-1900
205-2000 515-2200
150-430
570-1300
220-255
300-900
340-660
300
110-620
110

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Step 3: b) The load at which at he bar suffers permanent deformation:

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