The Material Failure Mode Prediction Calculator is a practical engineering tool designed to assess potential material failure mechanisms under different loading and operating conditions. Using established mechanical engineering formulas, this calculator helps engineers evaluate ductile yielding, brittle fracture, fatigue failure, elastic buckling, and creep-related failure. By entering material properties, stress conditions, and geometric parameters, users can calculate safety factors, utilization ratios, and preliminary failure risk levels. Ideal for mechanical engineers, material scientists, and structural designers, the Material Failure Mode Prediction Calculator supports material selection, structural integrity assessment, and mechanical component design optimization. Improve engineering efficiency, identify potential failure risks, and enhance product reliability with formula-based material failure analysis.

Calculation mode

Choose the failure criterion to calculate.

Failure mode

Brittle fracture approach
Strength screening compares principal stresses with Sut and Suc (brittle materials only). Fracture mechanics compares KI with KIC for a known or assumed crack.

Material and units

Selecting a material never fills in property values. Enter validated data for your exact grade, condition and temperature.

Ductile enables von Mises yielding; Brittle enables principal stress screening.
Identifies the material the entered data belong to.
Entered stresses are converted when you switch. 1 ksi = 6.894757 MPa.
If entered, each evaluated criterion is checked for n ≥ nreq.

Material properties

Only the properties needed by the selected mode are shown. Values must apply at the operating temperature.

Required for yielding. Optional elsewhere: enables the first-cycle yield, LEFM validity and inelastic buckling checks.
Used by brittle strength screening and the Goodman line. Never used as a substitute for fracture toughness.
Enter as a positive magnitude.
Elastic modulus at the operating temperature. 1 Msi = 10⁶ psi.
Valid plane-strain toughness (e.g. ASTM E399 or E1820) at the service temperature, thickness and loading rate.
Not every material has a true endurance limit. Aluminum alloys require a fatigue strength at a stated life.
Fully reversed value already corrected for surface, size, loading type, temperature and reliability. Not estimated automatically.
Cycle count at which the entered fatigue strength applies.
Rupture life is never estimated from temperature and stress alone.
From validated rupture data (for example a minimum or design rupture curve) for this temperature and stress.
P = T(C + log10 to) with T in kelvin and to in hours, read from the master curve at the applied stress.
Use the constant from the same data set (often near 20 for steels, but take it from the source).

Loading parameters

Tension is positive and compression is negative. Use local stresses at the critical location unless a field says otherwise. Section properties are entered directly; they are not derived from assumed shapes.

Enter 0 for a plane stress state. Principal stresses may be entered in any order.
The stress used in the definition of your geometry factor Y (usually the remote or nominal stress across the crack plane).
Cyclic stress input
Nominal stresses at the critical section for constant-amplitude, uniaxial cycling.
Applied to the nominal alternating stress. Leave blank (1.0) if the stresses are already local values.
Applies only when the mean stress is compressive.
Concentric axial load, entered as a positive magnitude.
Sustained stress magnitude that the rupture data correspond to.
Defined consistently with Y: e.g. depth of an edge crack, or half-length of a through centre crack.
Dimensionless. About 1.0 for a centre crack in a wide plate and about 1.12 for a shallow edge crack; take Y from a handbook solution for your geometry.
Length, area and second moment of area all use this unit. Entered values are converted when you switch.
Theoretical values for ideal supports. Real connections are rarely perfectly fixed.
Enables the slenderness ratio and the elastic-range check.
About the critical buckling axis, normally the axis with the smallest I for the same unbraced length.