When we compare three different materials (a steel alloy, an aluminium alloy and a composite material), what is the worst option for an aircraft application loaded in tension? (You may use the data of Table 1)
To determine the worst option for an aircraft application loaded in tension among a steel alloy, an aluminium alloy, and a composite material, we need to analyze the data in Table 1. As the table data is not provided, we cannot give a definitive answer without the specific material properties and characteristics of each option.
However, in general, steel alloys tend to have higher tensile strength and better fatigue resistance compared to aluminium alloys and composite materials. As aircraft applications often require high tensile strength to withstand the loads and stresses during operation, a composite material might typically be the worst option for tension-loaded aircraft applications. Nevertheless, this generalization would only be valid in the absence of specific data from Table 1.