Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of three triangular wing-fuselage models which differed only in wing thickness-chord ratio. The wings had an aspect ratio of 2.31 with 6-, 9-, and 12-percent-thick biconvex sections and a fuselage with a fineness ratio of 12. Results regarding the normal force, chord force, and pitching moment for various angles of attack.

This study soughs to determine the x-ray activity of two samples of stainless steel prepared from tubing used in the ANL-140, in-pile experiment (P-13). This information is necessary in order to predict the activity of the P-13 rig at the time of removal. The primary contribution to the over-all activity will be from Ta{sup 181} and Co{sup 59} impurities.

The process tube assembly functions to provide a water-cooled channel through the reactor into which uranium slugs are inserted for processing. The channel consists of a cylindrical tube with 2 ribs towards the bottom of the inside diameter which supports the slugs in a central location. Thus providing an annular space around the slugs for the cooling water used to remove the heat generated by fission of the uranium. Because of the relative movement between the graphite and the biological shield as the result of graphite growth and thermal expansion, the portion of the process tube which extends through the biological shields at the front and rear faces must be protected against sharp bends that would prevent movement of the slugs through the tube. This requires a design which will permit such relative movement, and maintain shielding around the opening through the shield. In addition, the process tube assembly requires provisions for introducing the cooling water flow at each tube at the inlet or front face and for discharging the coolant at the outlet or rear face. Provisions are also required for opening the tube at the inlet and outlet faces to charge and discharge the slugs. This paper discusses …

Second-order solutions of supersonic-flow problems are sought by iteration, using the linearized solution as the first step. For plane and axially symmetric flows, particular solutions of the iteration equation are discovered which reduce the second-order problem to an equivalent linearized problem. Comparison of second-order solutions with exact and numerical results shows great improvement over linearized theory.