The following report follows the studies of electroplating on uranium and concurrent metallurgical clodding.

In accordance with the policy that a centralized inventory shall be kept of all radioactive waste liquid discharged to ground, it is recommended that the volumes of condensate from the SX-farm, the dates or periods of discharge, and the activity densities of radioisotopes in the condensate discharged be determined by Separations Section and reported regularly to the Radiological Standards Unit. This paper is a description of the condensate system, with recommendations for sampling and analysis.

Report presenting an investigation in a mixing-zone apparatus to determine the effects of jet flow on two-dimensional base pressure and the development of supersonic channel flow about a two-dimensional base, with and without splitter plates of different thicknesses. Results regarding the starting cycle for outer streams only, the fully established supersonic flow, and the base pressure between the center jet and outer streams are provided.

Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.

"In order to determine the factors involved in the scale-up of cores with concentric inlet and outlet pipes, a 48 inch carbon steel flow model, geometrically similar to a 6 foot diameter core, has been assembled and tested...Visual studies were made of dye and gas behavior in the sphere, and quantitative measurements of point residence times were obtained through the use of conductivity cells actuating a Brush recorder. Static pressure drop across the core was measured."

Report presenting an investigation at subsonic, transonic, and supersonic speeds of the effect of lip shape on drag, pressure recovery, and mass flow of a nose-inlet air-induction system. Four lips of varying degrees of bluntness were tested on a fuselage model at a range of Mach numbers and angles of attack. Results regarding pressure recovery, net drag, and analysis are provided.

Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.