Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the control effectiveness and hinge-moment characteristics for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Pressure distribution and hinge-moment measurements were made at a range of angles of attack and control deflections. Results regarding effect of control deflection, effect of wing angle of attack, effect of Reynolds number, effect of trailing-edge thickness, effect of hinge-line gap, effect of Mach number, and effect of control size and location are provided.

The useful lifetimes of the phosphoric-hydrochloric anodic etching solution and the nitric acid stripping solutions were studied. Groups of uranium wafers of surface areas approximately 0.033 sq ft were anodically etched and stripped. From the losses in weight observed, it was concluded that at least three square feet of uranium may be anodized per liter of phosphoric-hydrochloric acid solution without regeneration. The nitric acid stripping solution was found to be satisfactory for at least one square foot of uranium per liter, but the reaction rate decreased rapidly after the treatment of two square feet per liter.

Report presenting an investigation of the validity of application of the simplified-radial-equilibrium equation to axial-flow turbomachines. Two different types of equations were used. Results regarding the interpretation of the data, single stages, middle and end stages of the multistage compressor, application of the radial-equilibrium equation, and the solution for the velocity distributions are provided.

A discussion of pertinent items related to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters. The following items are emphasized: controllable exit and ram recovery for reciprocating-engine cooling, performance penalties possible in turbine-engine installations, the effects of high subsonic flow velocities on the performance of duct elements, and the effects of centrifugal forces on the flow in a ducted helicopter rotor.

Abstract: In one of the final stages of the process at the Mallinckrodt Uranium Refining Center, a 45 per cent nitric acid solution at about 170 F is used to pickle the calcined magnesium fluoride scale off the uranium derbies. The increase in the fluoride-ion content of the bath tends to promote corrosion of the Type 347 stainless tanks. This attack becomes excessive if 0.3 g/liter of fluoride ion or more is present. It was found that if aluminum ion is added to the solution the corrosiveness of the bath can be controlled. Two or three times as much aluminum ion as fluoride ion present is found satisfactory at 170 F. Indications are that the tying up of the fluoride-ion by the complexion [AlF6]8 is responsible for the corrosion control.

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A method for determining dissolver solution concentration as a function of length of column traversed for trickletype continuous dissolvers has been developed. An illustrative example is worked out for the mercury-catalyzed nitric acid dissolution of U-Al cast alloy slugs. The method employs a graphical integration of simple functions of dissolution rates and acid concentrations. These rates and concentrations are easily obtained from batch experiments made over the important ranges of concentration. (auth)

"Results are reported of current studies at the Forest Products Laboratory to develop a metal-bonding adhesive with greater resistance to temperatures up to 600 degrees Fahrenheit that is easier to use than present ones. Most promising is a formulation of phenol and epoxy resins modified with hexamethylenetetramine and supplied for use as a dry tape supported on a glass-mat base" (p. 1).

Memorandum presenting an exploratory investigation in the 9- by 12-inch blowdown tunnel to determine the effect of inboard spoilers located along the 20- and 30-percent-chord lines on the static longitudinal stability characteristics of a semispan 45 degree sweptback wing-body combination with a leading-edge chord-extension. The model pitching-moment characteristics were improved by spoilers extending from 15 percent semispan to 45 percent semispan. Results regarding pitching moment, lift, drag, rolling moment, and lateral center of pressure are provided.

Report presenting an investigation of the effect of yaw and angle of attack on the total-pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet designed to have low external drag at a Mach number of 2.7 and an angle of attack of 0 degrees. Total-pressure recovery and mass-flow data are presented for a Mach number of 2.71 at angles of yaw 0, 2.5, and 5 degrees and angles of attack of 0 and 5 degrees are provided.

Report presenting data for five diffusers tested with and without vortex-generator controls in order to determine the performance improvements attainable through the use of boundary-layer controls. Results regarding inlet conditions, axial inlet flow, and whirling inlet flow are provided.

Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.

"The following is an evaluation of a modified Zircaloy-2 ingot melted at WAPD using the non-consumable electrode melting technique. The nominal composition of the alloy is 0.5% tin, 0.1% iron, 0.1% chromium, and 0.5% nickel."

Report discussing an investigation of a fingered semaphore spoiler and an equivalent solid spoiler configuration to determine the effects of spoiler projection, porosity, and chordwise position on the rolling effectiveness and drag of spoiler arrangements at a range of Mach numbers. The fingered semaphore spoilers were found to have less rolling effectiveness and drag than the solid spoilers.

"A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift" (p. 1).

From Summary: "A 1/5-scale, rocket-propelled model of the Convair F-102 configuration was tested in free flight to determine zero-lift drag at Mach numbers up to 1.34 and at Reynolds numbers comparable to those of the full-scale airplane. This large-scale model corresponded to the prototype airplane and had air flow through the duct. Additional zero-lift drag tests involved a series of small equivalent bodies of revolution which were launched by means of a helium gun."

Herman Lurie's weekly report for the sugar market.

Herman Lurie's weekly report for the sugar market.

Herman Lurie's weekly report for the sugar market. Details include prices, distribution, sugar tons, and refiners.

Daily cash report for Imperial Sugar Company including a list of large withdrawls for the months surrounding the date showing the daily expenses and estimated balance for each entry. It also lists scheduled payments for bank loans.

Imperial Sugar Company memorandum for minutes of a regular meeting of directors.

With the assumption of infinite conductivity a simple model may be constructed for the dynamic construction of a current carrying plasma, i.e., the pinch effect. The magneto-hydrodynamic equations of this model are discussed and solved. It is also shown that the infinite conductivity model can be derived from a picture of particles orbiting without collisions in the fields set up by their motions.

Report presenting information regarding the feasibility of using a rectangular free water jet to obtain hydrodynamic data at very high speeds. Total-head pressure distributions in the jet and experimental hydrodynamic lift data is provided and compared to data obtained in water tank testing. The data obtained indicates that it is feasible to use a free water jet for this purpose.

"The effects of elevator deflections from 0 degrees to -20 degrees on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane with chordwise fences have been determined at Mach numbers from 0.6 to 1.1 for angles of attack up to 20 degrees in the Langley 8-foot transonic tunnel. The configuration exhibited static longitudinal stability throughout the range tested, although a mild pitch-up tendency was indicated at Mach numbers from 0.85 to 0.95. Elevator pitch effectiveness decreased rapidly between the Mach numbers of 0.9 and 1.0, however, no complete loss or reversal was indicated for all conditions tested" (p. 1).