o (MPa) 750 B F 600 A parallel Ty = 450 300 150 D C 0.01 0.02) 0.03 0.04 = 0.006 e (mm/mm) 0.023 EOC- The stress-strain diagram for an aluminum alloy that is used for making aircraft parts is shown in Fig. 3-19. If a specimen of this material is stressed to 600 MPa, determine the permanent strain that remains in the specimen when the load is released. Also, find the modulus of resilience both before and after the load application.
o (MPa) 750 B F 600 A parallel Ty = 450 300 150 D C 0.01 0.02) 0.03 0.04 = 0.006 e (mm/mm) 0.023 EOC- The stress-strain diagram for an aluminum alloy that is used for making aircraft parts is shown in Fig. 3-19. If a specimen of this material is stressed to 600 MPa, determine the permanent strain that remains in the specimen when the load is released. Also, find the modulus of resilience both before and after the load application.
Materials Science And Engineering Properties
1st Edition
ISBN:9781111988609
Author:Charles Gilmore
Publisher:Charles Gilmore
Chapter6: Introduction To Mechanical Properties
Section: Chapter Questions
Problem 6.5P
Related questions
Question
![o (MPa)
750
B
-F
600
A
parallel
Ty = 450
300
150
D
€ (mm/mm)
0.01 | 0.02) 0.03 0.04
Ey = 0.006
- EOC-
O7
0.023
The stress-strain diagram for an aluminum alloy that is used for
making aircraft parts is shown in Fig. 3-19. If a specimen of this
material is stressed to 600 MPa, determine the permanent strain
that remains in the specimen when the load is released. Also, find
the modulus of resilience both before and after the load
application.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F8f8500b6-6968-4c64-88de-d61c630cdf56%2Feae51c6f-dc9a-422b-81b9-f10a69bd8195%2Fdd9235i_processed.jpeg&w=3840&q=75)
Transcribed Image Text:o (MPa)
750
B
-F
600
A
parallel
Ty = 450
300
150
D
€ (mm/mm)
0.01 | 0.02) 0.03 0.04
Ey = 0.006
- EOC-
O7
0.023
The stress-strain diagram for an aluminum alloy that is used for
making aircraft parts is shown in Fig. 3-19. If a specimen of this
material is stressed to 600 MPa, determine the permanent strain
that remains in the specimen when the load is released. Also, find
the modulus of resilience both before and after the load
application.
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