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Representative tensile and compressive stress-strain curves are give for each material at the test temperatures. The variations of the tensile and compressive properties with temperature is shown for specimens tested parallel and transverse to the rolling direction of the materials. Secant and tangent moduli, obtained from the compressive data, are included.
This investigation was conducted to determine mechanical properties of several high performance alloys at room and elevated temperatures. The effects of temperature (up to 1900 F) and exposure (up to 1000 hours) at temperature on the tensile, compressive, bearing and shear properties were determined from measured stress-strain information in both the elastic and plastic range. The following materials were considered: 301 extra hard stainless steel; Ph157Mo(TH 1050); AM 355; Rene 41; and N-155. All material was from 0.050-inch sheet, except the material for the 1/8-inch diameter shear pins, which were fabricated from 1/4-inch plate. Heat treatment was in accordance with existing specifications for the materials, or other procedures approved by ASD to develop the optimum strength properties. Descriptions of the test specimens, equipment, and procedures are included. Test results are reported in tables and in curves showing the effects of temperature and time on the various mechanical properties.
Results of tensile stress-strain tests and completely reversed sheet-bending fatigue tests conducted at room temperature on unnotched sheet specimens of Ta-lOW tantalum alloy, D-3l niobium alloy, pure tungsten, and Mo-0.5Ti molybdenum alloy are presented. Fatigue data from tests on similar specimens of 2024-T3 aluminum alloy and 17-7 PH stainless steel are compared with previous data from axial-load tests on larger specimens of these materials to determine whether the small size of the specimens used in this investigation produces representative results. Comparisons of the various materials on the basis of applied-stress- ultimate-strength and strength-density ratio also are presented.
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.