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2 answers:
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Answer:
fracture will occur since ( 31.8 Mpa√m ) is greater than the of the material ( 30 Mpa√m )
Explanation:
Given the data in the question;
To determine whether the aircraft component will fracture, given a fracture toughness of 30 Mpa√m, stress level of 355 and maximum internal crack length of 1.39 mm.
On a similar component, it has been said that fracture results at a stress of 237 MPa when the maximum (or critical) internal crack length is 2.78 mm.
so we first of all solve for the parameter Y in the condition where fracture occurred.
= 30 Mpa√m
σ = 237 MPa
2α = 2.78 mm = 2.78 × 10⁻³ m
so
Y = / σ√πα
we substitute
Y = (30 Mpa√m) / (237 MPa)√(π(2.78 × 10⁻³ m / 2 ) )
Y = (30 Mpa) / (237)( 0.06608187 )
Y = 30 / 15.6614
Y = 1.9155
Next we solve for Yσ√πα for the second case;
σ = 355 Mpa, 2α = 1.39 mm = 1.39 × 10⁻³ m
so
Yσ√πα = 1.9155 × 355 Mpa × √( π × (1.39 × 10⁻³ m / 2) )
= 1.9155 × 355 × 0.0467269
= 31.8 Mpa√m
so
( 31.8 Mpa√m ) > ( 30 Mpa√m )
Therefore, fracture will occur since ( 31.8 Mpa√m ) is greater than the of the material ( 30 Mpa√m )
Answer:
1788.9 MPa
Explanation:
The magnitude of the maximum stress (σ) can be calculated usign the following equation:
<u>Where:</u>
<em>ρ: is the radius of curvature = 2.5x10⁻⁴ mm (0.9843x10⁻⁵ in)</em>
<em>σ₀: is the tensile stress = 100x10⁶ Pa (14500 psi) </em>
<em>2a: is the crack length = 4x10⁻² mm (1.575x10⁻³ in) </em>
Hence, the maximum stress (σ) is:
Therefore, the magnitude of the maximum stress is 1788.9 MPa.
I hope it helps you!