Abstract
The characteristics of a new material, commonly known as stainless steel, are considered, with facts and conclusions concerning its adaptability and suitability for use in aircraft construction. The type of steel discussed is called 18-8, by the proportions of chromium and nickel used. This material is selected because it is austenitic in character and is more readily procurable than some of its kindred alloys. The strength-to-weight ratios of 18-8 stainless steel are first considered in relation to comparable values from aluminum alloy, which is the most widely used metal in aircraft structures. This comparison is made using four criteria as representing the value of a material for structural uses. These criteria are (1) tensile strength, (2) the strength of columns, (3) the strength of members in bending, and (4) the deflection or stiffness characteristics. In this connection the finishes which are necessarily employed on aluminum alloy as corrosion preventives are charged against that material.
