From summary: "This report covers an experimental investigation into the fabrication of various potential fuel-element materials and the testing of these materials for compatibility with structural metals at 1090 C (2000 F)."

Technical report outlining the rate of production of modified MTR type fuel elements for the Bulk Shielding Facility has proceeded. Includes compatibility test that were started as a guide in the selection of materials suitable for fuel-element fabrication. [From Summary]

Technical report covering experiments to measure the resonance and absorption of neutrons in U238 cylinders. Report also discusses control problems connected to the Bulk Shielding Facility and work on MTR controls.

Technical report presenting a summary of the flowsheets, equipment, and progress for the Oak Ridge National Laboratory (ORNL) pilot plant development of the Purex Process and of the ORNL Metal Recovery Program. As of this report, conversion of the Purex pilot plant equipment in Buildings 3019 and 3503 is 90% complete. The building structure for the ORNL Waste Metal Recovery plant had been completed, and 15% of the process equipment had been installed. The first hot runs for this plant were scheduled for June, 1951. [From Abstract; Introduction]

Report documenting the suitability of Missouri for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.

"Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section" (p. 1).

Memorandum presenting calculations made to determine the deceleration at any time after jettisoning of an airplane nose-section design typical of those which have been proposed as escape devices for high-speed airplanes. The decelerations were determined by two methods, one using successive approximations requiring graphical integration and the other giving reasonably close approximations by direct computation.

Report presenting an investigation at a Mach number of 1.24 using the NACA wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a scale semispan model of the variable-sweep Bell X-5 airplane with the wind swept back at several different degrees. Lift, drag, and pitching moments were obtained for various angles of attack for several horizontal tail settings and with the tail off for each angle of sweep of the wing.

Memorandum presenting a group of alkylsilanes consisting of monoethylsilane, diethylsilane, and trimethylsilane prepared in 65- and 90-percent yield by reduction of the respective alkylchlorosilanes with either lithium hydride or lithium aluminum hydride. The boiling points, densities, refractive indices, and freezing points were determined and presented with a survey of literature values.

Report presenting sound measurements at static conditions for a two-blade, 47-inch-diameter propeller over a range of tip Mach numbers. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. Results regarding the experimental results and comparison with theory are provided.

"The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).

Report presenting the results of nine experimental flutter tests involving two flat-plate models and two rib and spar models of NACA 0012 airfoil sections in order to give a comparison of the flutter characteristics of wings with M and W type plan forms. The W plan form generally gave higher flutter speeds than the M plan forms.

Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick double-wedge airfoil.

Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.

Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.

From Summary: "An empirically derived basis for predicting the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The concepts involved represent an initial step toward the development of a calculation technique which is generally applicable to the design of thermal ice-prevention equipment for airplane wing and tail surfaces. It is shown that sufficiently accurate estimates, for the purpose of heated-wing design, can be obtained by a few numerical computations once the velocity distribution over the airfoil has been determined. The calculation technique presented is based on results of extensive water-drop trajectory computations for five airfoil cases which consisted of 15-percent-thick airfoils encompassing a moderate lift-coefficient range."

From summary: "The methods of calibrating the 305 pile for impurities and density differences in graphite are reviewed and calibration constants are calculated theoretically."

Abstract: "The potential of the Np(IV)-Np(V) couple is not directly measurement since the couple does not establish reversible equilibrium at an inert electrode. Reproducible potential measurements were obtainable, however, in solutions containing Np(IV), Np(V), Pe(II), and Pe(III) ions in oxidation-reduction equilibrium. The expected fourth power hydrogen ion dependence of the Np(IV)-Np(V) couple was confirmed over the range 0.25-1.0 molar perchloric acid concentration. The heat of the reaction NpO2+ + 1/2 H2 + 3H+ = Np-(+4) + 2 H2O in 1 molar perchloric acid solution was determined from the electromotive force temperature coefficient to be -36.3 +/- 0.3 kg.-cal. The formal potential of the Np(IV)-Np(V) couple is -0.746 v. at 25 degrees in 1 molar perchloric acid solution."

Since the 25 content of the uranium to be used in a MTA multiplying lattice is quite uncertain at present, it is necessary to assume various degrees of depletion in order to estimate the multiplication constant K-o and the production of 49 in an infinite uranium-graphite lattice

The pressure and temperature cycles developed during the bomb reduction of uranium tetrafluoride by calcium have been determined. Data for the 250, 500, and 1000 gram scale reductions are given, and the apparatus used is described.

Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.

"This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent data from laboratory researches, single-combustor studies, and full-scale engine investigations are presented on each phase of the starting problem" (p. 1).

Technical report covering experiments happening on the Analytical Chemistry Division's sites at the Oak Ridge National Laboratory. Includes information on ionic analyses, radio-chemical analyses, spectrochemical analyses, service analyses, inorganic preparations, analytical chemical control of homogeneous reactor solution, optical and electron microscopy, and service analyses for the period ending March 26, 1951. [From Abstract]