Fracture Toughness
Fracture toughness is an indication of the amount of stress required to propagate a preexisting flaw. It is a very important material property since the occurrence of flaws is not completely avoidable in the processing, fabrication, or service of a material/component. Flaws may appear as cracks, voids, metallurgical inclusions, weld defects, design discontinuities, or some combination thereof. Since engineers can never be totally sure that a material is flaw free, it is common practice to assume that a flaw of some chosen size will be present in some number of components and use the linear elastic fracture mechanics (LEFM) approach to design critical components. This approach uses the flaw size and features, component geometry, loading conditions and the material property called fracture toughness to evaluate the ability of a component containing a flaw to resist catastrophic fracture.
A parameter called the critical stressintensity factor (K_{C}) is used to represent the fracture toughness of most materials. A Roman numeral subscript indicates the mode of fracture and the three modes of fracture are illustrated in the image to the right. Mode I fracture is the condition in which the crack plane is normal to the direction of largest tensile loading. This is the most commonly encountered mode and, therefore, for the remainder of the material we will consider K_{I}
The stress intensity factor is a function of loading, crack size, and structural geometry. The stress intensity factor may be calculated by the following equation:
$K_{I}=\sigma \beta \sqrt{\pi a }$
Where:  K_{I}  is the stress intensity factor in $\mathrm{MPa}/\sqrt{\mathrm{m}}$ or $\mathrm{psi}/\sqrt{\mathrm{in}}$ 
σ  is the applied stress in MPa or psi  
β 
is a dimensionless correction factor depends on specimen geometry.


a  is the crack length in meters or inches 
The fracture toughness K_{C} of a material is defined as the critical stress intensity factor for immediate crack growth under given conditions. Under prescribedload boundary conditions, such crack growth will be immediately catastrophic. Any flaw large enough (length a) that its stress intensity K_{I} might reach K_{C} under the loading σ may cause immediate failure.
In larger objects the applied load for catastrophic fracture may be significantly lower than expected from the the nominal ultimate strength of the material. As such, catastrophic fracture is often the limiting factor in engineering design. In addition, repeated stress intensities K_{I} which do not reach K_{C} can still cause slow crack growth due to fatigue.
Role of Material Thickness
Specimens having different thickness produce different values for K_{C}. Thin specimens cannot have stress components normal to their free surfaces, whereas the inside of thicker specimens may be constrained by surrounding material and develop stress components in the thickness dimension. Such thin specimens have a higher value of K_{C} because they have a much larger plastic zone area than thicker specimens, spreading the fracture energy over that larger area. The value of K_{C} decreases with thickness until the the thickness exceeds some critical dimension. At this point the value of K_{I} becomes relatively constant and this value, K_{IC}, is a true material property which is called the planestrain fracture toughness. K_{IC} is usually measured by the process specified in ASTM Standard E399. The relationship between stress intensity, K_{I}, and fracture toughness, K_{IC}, is similar to the relationship between stress and tensile stress. The stress intensity, K_{I}, represents the level of “stress” at the tip of the crack. The fracture toughness, K_{IC}, is the highest value of stress intensity that a material under very specific (planestrain) conditions can withstand without fracture. As the stress intensity factor reaches the K_{IC} value, unstable fracture occurs. As with a material’s other mechanical properties, K_{IC} is commonly reported in reference books and other sources.
Plane Strain  a condition of a body in which the displacements of all points in the body are parallel to a given plane, and the values of theses displacements do not depend on the distance perpendicular to the plane
Plane Stress – a condition of a body in which the state of stress is such that two of the principal stresses are always parallel to a given plane and are constant in the normal direction.
PlaneStrain and PlaneStress
When a material with a crack is loaded in tension, the materials develop plastic strains as the yield stress is exceeded in the region near the crack tip. Material within the crack tip stress field, situated close to a free surface, can deform laterally (in the zdirection of the image) because there can be no stresses normal to the free surface. The state of stress tends to biaxial and the material fractures in a characteristic ductile manner, with a 45^{o} shear lip being formed at each free surface. This condition is called “planestress" and it occurs in relatively thin bodies where the stress through the thickness cannot vary appreciably due to the thin section.
However, material away from the free surfaces of a relatively thick component is not free to deform laterally as it is constrained by the surrounding material. The stress state under these conditions tends to triaxial and there is zero strain perpendicular to both the stress axis and the direction of crack propagation when a material is loaded in tension. This condition is called “planestrain” and is found in thick plates. Under planestrain conditions, materials behave essentially elastic until the fracture stress is reached and then rapid fracture occurs. Since little or no plastic deformation is noted, this mode of fracture is termed brittle fracture.Fracture Energy Release Rate or Work of Fracture
The fracture energy release rate (or equivalently work of fracture) G_{C} of a material is an alternate form sometimes used in place of the critical stress intensity factor K_{C}. The relationship between G_{C} and K_{C} is
$G_{C}=K_{C}^{2}/E^{*}$where E^{*} is an equivalent modulus:
$E^{*}=E$ for plane stress;
$E^{*}=E$ for plane strain cases such as material property G_{IC} and K_{IC} values.
PlaneStrain Fracture Toughness Testing
When performing a fracture toughness test under ASTM E399, the most common test specimen configurations are the single edge notch bend (SENB or threepoint bend), and the compact tension (CT) specimens. From the above discussion, it is clear that an accurate determination of the planestrain fracture toughness requires a specimen whose thickness exceeds some critical thickness (B). Testing has shown that planestrain conditions generally prevail when:
$B\geq2.5\left(\frac{K_{IC}}{\sigma_{y}}\right)^{2}$
Where:  B  is the thickness, constrained to produce plane strain conditions for most of the crack 
K_{IC}  is the fracture toughness of the material  
σ_{y}  is the yield stress of material 
When a material of unknown fracture toughness is tested, a specimen of full material section thickness is tested or the specimen is sized based on a prediction of the fracture toughness. If the fracture toughness value resulting from the test does not satisfy the requirement of the above equation, the test must be repeated using a thicker specimen. In addition to this thickness calculation, test specifications have several other requirements that must be met (such as the size of the shear lips) before a test can be said to have resulted in a K_{IC} value.
When a test fails to meet the thickness and other test requirement that are in place to insure planestrain condition, the fracture toughness values produced is given the designation K_{C}. Sometimes it is not possible to produce a specimen that meets the thickness requirement. For example when a relatively thin plate product with high toughness is being tested, it might not be possible to produce a thicker specimen with plainstrain conditions at the crack tip.
PlaneStress and TransitionalStress States
For cases where the plastic energy at the crack tip is not negligible, other fracture mechanics parameters, such as the J integral or Rcurve, can be used to characterize a material. The toughness data produced by these other tests will be dependent on the thickness of the product tested and will not be a true material property. However, planestrain conditions do not exist in all structural configurations and using K_{IC} values in the design of relatively thin areas may result in excess conservatism and a weight or cost penalty. In cases where the actual stress state is planestress or, more generally, some intermediate or transitionalstress state, it is more appropriate to use J integral or Rcurve data, which account for slow, stable fracture (ductile tearing) rather than rapid (brittle) fracture.
Uses of PlaneStrain Fracture Toughness
K_{IC} values are used to determine the critical crack length when a given stress is applied to a component.
$\sigma_{c}\leq\left(\frac{K_{IC}}{Y\sqrt{\pi a}}\right)$
Where:  σ_{c}  is the critical applied stress that will cause failure 
K_{IC}  is the planestrain fracture toughness  
Y  is a constant related to the sample's geometry  
a  is the crack length for edge cracks or one half crack length for internal crack 
K_{IC} values are used also used to calculate the critical stress value when a crack of a given length is found in a component.
The critical flaw size (length of a flaw that will grow catastrophically) is then: $a_{c}=\frac{1}{\pi}\left(\frac{K_{IC}}{\sigma Y}\right)^{2}$
Where:  a_{c}  is the length of the critical crack for edge cracks or one half the length of the critical internal crack 
σ  is the stress applied to the material  
K_{IC}  is the planestrain fracture toughness  
Y  is a constant related to the sample's geometry 
Orientation
The fracture toughness of a material commonly varies with grain direction. Therefore, it is customary to specify specimen and crack orientations by an ordered pair of grain direction symbols. The first letter designates the grain direction normal to the crack plane. The second letter designates the grain direction parallel to the fracture plane. For flat sections of various products, e.g., plate, extrusions, forgings, etc., in which the three grain directions are designated (L) longitudinal, (T) transverse, and (S) short transverse, the six principal fracture path directions are: LT, LS, TL, TS, SL and ST.