Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.

Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.

This quarterly progress details ongoing research at the Oak Ridge National Laboratory as a part of the Aircraft Nuclear Propulsion Project. Topics discussed include reactor theory and design, [part two is not included], materials research, and appendixes with information on analytical chemical studies.

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Abstract: "The effect of variation in fuel element density upon f, p in a D2O cooled and moderated lattice of cylindrical fuel elements is investigated. The CP-3 lattice is chosen as a reference. The effect of a source term in the fuel element is considered. f, p are calculated as functions of "a", the ratio of the modified fuel element density to the original (fuel only) density. Curves showing f(a), p(a) are included. It is concluded that a 1 per cent decrease in the product, f(d), p(a) is not suffered until a=0.3. A 5 per cent decrease in k is estimated at a-0.4. The necessity of introducing the fuel element source term into the calculation after a has been decreased to about 0.6 is brought out."

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Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.

Report presenting an investigation of the effects of tip-mounted jet-engine nacelles on the aerodynamic characteristics of low-aspect-ratio rectangular and tapered wings using the transonic-bump technique. The effect of the tip-mounted nacelles was generally to increase the lift-curve slopes for wings of aspect ratio 2 or larger with upper or lower mounted nacelles causing larger increases than symmetrically mounted nacelles. Results regarding rectangular wings and tapered wings are provided.

Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.

Report presenting a wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and some of the difficulties involved in obtaining extensive laminar flow are provided.

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.

"An investigation of the isothermal wake-flow characteristics of several flame-holder shapes was carried out in a 4- by 4-inch flow chamber. The effects of flame-holder-shape changes on the characteristics of the Karman vortices and thus on the recirculation zones to which experimenters have related the combustion process were obtained for several flame holders. The results may furnish a basis of correlation, of combustion efficiency and stability for similarly shaped flame holders in combustion studies" (p. 1).

From introduction: "A study of the fission product activity-fixing properties of the Savannah River Project soils was undertaken by this site to provide data for the planning of the waste disposal program for the Savannah River Project."

Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.

Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.

Ducks, geese, coots, and other wild birds, both migratory and resident, have been swimming on the Redox waste water pond and eating the herbage and mud on the bottom. The pond is caused by the discharge of five to ten million gallons of water a day from the heating and cooling coils of reactor vessels in the Redox plant. At least twice in recent months leaks in the coils have permitted solutions of radioactive material to escape to the swamp. Once the leak was in the waste concentrator tank and once in the first oxidation tank, so that the material in the swamp would include significant amounts of every radioisotope found in irradiated uranium, including plutonium and all fission products. This paper discusses the hazards to humans from handling or eating wildfowl and to risk of both internal and external exposure.

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It is the intent of this report to summarize Reactor Unit`s progress on RDA-DC-3 and Program X from the date of inception, October 6, 1951, through January 12, 1952. The report is divided into four sections covering: (1) basic reactor criteria; (2) process unit design; (3) building and services design; (4) electrical.

Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.

Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.

From Summary: "An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach number from about 0.69 to 0.99, at Reynolds numbers of about 4.1 x 10(exp 6) to 4.7 x 10(exp 6), and through an angle-of-attack range up to 1.5 deg at lower speeds and up to 5 deg at the highest speed."