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Static tests on paper cylinders were conducted to obtain qualitative information in connection with a study of the strength of stressed-skin fuselages. The effects of radius-thickness ratio and bulkhead spacing were investigated with the cylinders in compression, bending, combined bending and shear, and torsion.
The effects of scale and turbulence on the lift and drag of five airfoils, the N.A.C.A. 0006 , the N.A.C.A. 0021, the Clark Y, The U.S.A 35-A, and the U.S.N. P.S.6, hve been investigated in the Variable Density Wind Tunnel. Tests were made over a wide scale for only two different conditions of turbulence.
The variation of the coefficient of discharge with the length-diameter ratio of the orifice was determined for nozzles having single orifices 0.008 and 0.020 inch in diameter. Ratios from 0.5 to 10 were investigated at injection pressures from 500 to 5,000 pounds per square inch.
Although a number of investigations of the bearing strength of aluminum alloys have been made, the problem remains one of considerable interest to the aircraft industry. For this reason it has seemed advisable to make additional tests of the commonly used aircraft alloys in an effort to establish a better basis for the selection of allowable bearing values. Current design practice does not recognize the effect of edge distance upon bearing strengths, and for this reason edge distance upon bearing strengths, and for this reason edge distance was one of the principal variables considered in this investigation. The increasing emphasis being placed upon permanent set limitations makes it essential that more information on bearing yield phenomena be obtained.
Chiefly translations from foreign aeronautical journals.