From introduction: "The present investigation of the properties of boron stainless steel is an outgrowth of a project started in 1947. The problem is to replace the present steel used for drop rods in the Hanford piles with a material much less subject to corrosive attack from the humid atmosphere existing at the location of the rods."

Report presenting an investigation at transonic speeds in the high speed tunnel to determine the rolling-effectiveness characteristics of several aileron arrangements for use on a 42 degree sweptback wing. Results regarding the rolling-moment coefficients, variation of coefficient with Mach number, outboard cusp aileron, and use of the leading-edge flaps are provided.

Performance characteristics of conical jet nozzles were determined in an investigation covering a range of pressure ratios from 1.0 to 2.8, cone half-angles from 5 degrees to 90 degrees, and outlet-inlet diameter ratios from 0.50 to 0.91. All nozzles investigated had an inlet diameter of 5 inches. The flow coefficients of the conical nozzles investigated were dependent on the cone half-angle, outlet-inlet diameter ratio, and pressure ratio. The velocity coefficients were essentially constant at pressure ratios below the critical. For increasing pressures above critical pressure ratio, there was a small decrease in velocity coefficient that was dependent on pressure ratio and independent of cone half-angle and outlet-inlet diameter ratio. Therefore the variation in performance (air flow and thrust) of several nozzles, selected for the same performance at a particular design condition, was proportional to the ratio of their flow coefficients.

"Results of an investigation by the free-fall method are presented herein for a configuration having a body of revolution of fineness ratio 12 and 45 degrees sweptback wing mounted aft of the maximum diameter of the body. The fillets were designed to provide large increases in the sweep of the leading edge and the line of maximum thickness as the wing root was approached. Comparison of these results with those for the same configuration without fillets shows that the addition of wing fillets increased the total drag of the configuration by about 35 percent at Mach numbers near 1.0 and about 15 percent at Mach numbers near 1.2" (p. 1).