Report presenting the results from tank landing and take-off tests with a dynamic model of a hypothetical jet-propelled airplane equipped with NACA hydro-skis. Results regarding landing tests, take-off tests, and practical considerations for the creation of hydro-ski configurations are provided. The hydro-skis suitable for flush retraction into streamline fuselages do appear to offer a practical means of water take-offs and landings.

Report presenting an analysis of the spanwise loading using two different methods on the wing of an airplane for which pressure-distribution measurements were available from flight tests up to a Mach number of 0.866. A comparison between measured and calculated distributions was made on the basis of equal wing-panel normal-force coefficients.

Report presenting an investigation of icing and ice protection at the inlet of a turbojet engine in the altitude wind tunnel. A method of ice protection was studied that uses hot gas bled from a turbine inlet and injected into the air stream ahead of the compressor inlet. Ice was either prevented or accumulated slowly at various engine speed levels.

Report presenting an investigation of a swept, rectangular, supersonic scoop inlet designed to have low external drag at the design Mach number of 2.7. The inlet was tested with two simulated fuselages with circular and rectangular cross sections. Results regarding shadow photographs, pressure recovery, wedge effects, drag, boundary-layer control, Mach number distribution in diffuser, wedge loads, aspect-ratio effects, and applicability of results are provided.

Report presenting an investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing in the Langley high-speed tunnel by means of the transonic bump technique. Three ailerons were investigated, one with a basic wing-plan form and two with an extended-tip plan form. Results regarding the longitudinal aerodynamic characteristics, rolling-moment data, control effectiveness, and lift effectiveness are provided.

Report presenting an investigation at low speed to determine the lateral-control and hinge-moment characteristics of a 20-percent-chord unsealed partial-span outboard aileron with several plan forms. Results regarding the wing aerodynamic characteristics are also provided.

Memorandum presenting the effective downwash characteristics of a wing-body configuration and the body alone determined from lift measurements of a horizontal tail located 0.333 and 0.479 wing semispan above the body center line. The wing had a sweepback angle of 47 degrees, an aspect ratio of 3.5, a taper ratio of 0.2, and a thickness ratio of 0.06.

From Summary: "A blade-element theory for axial-flow compressors has been developed and applied to the analysis of the effects of basic design variables such as Mach number, blade loading, and velocity distribution on compressor performance. The relations among several efficiencies useful in compressor design are derived and discussed. The possible gains in useful operating range obtainable by the use of adjustable stator blades are discussed and a rapid approximate method of calculating blade-angle resettings is shown by an example."

"A free-flight investigation into the effect of fuselage gloves, or load increases in volume, designed to improve the overall longitudinal area distribution of a swept-wing-body combination revealed that a reduction of about 20 percent in maximum pressure drag was obtained. The drag reduction effected by the use of gloves decreased with increasing Mach number, becoming zero at a Mach number of about 1.35, the limit of the experiments" (p. 1).

Report presenting a new blade series designed to operate at near choking inlet Mach numbers and to have near maximum critical Mach numbers by employing high aerodynamic loading of the profiles in the leading-edge region and relatively straight trailing edges. Results regarding the aerodynamic characteristics and prediction of high-speed performance are provided.

Memorandum presenting low-lift drag and longitudinal trim data for two versions of an interceptor-type airplane, the second of which had a slimmer nose and a thinner tail than the first. Data are presented for three models (complete, wingless, and horizontal tailless) of the first version, and from one model (complete configuration) of the second version. Results regarding longitudinal trim, drag, longitudinal stability, and flutter and buffet are provided.

The following report notes a general formula for the determination of the effect of atomic motion on nuclear cross sections, and evaluate the expression exactly in a few cases of interest.

Technical report describing work on two special projects: (1) the Oak Ridge Computer; and (2) numerical integration of differential equations; multipoint boundary problems. The reports also describes work on thirty special problems.

Technical report outlining the building status, crystal physics, solid state reactions, radiation metallurgy, engineering properties, and liquid fuels activities of the Physics of Solids Institute in period ending April 30, 1951. [From Introduction and Summary]

Report issued by the Oak Ridge National Laboratory discussing annual progress made by the Solid State Division. Work and research progress made during 1957 is presented. This report includes tables, illustrations, and photographs.

"An altitude-wind-tunnel investigation has been made to determine the performance of a Curtiss 732-1C2-0 four-blade propeller on a YP-47M airplane at high blade loadings and engine power. Propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and .50" (p. 1).

"An investigation was conducted in the Cleveland altitude wind tunnel to determine the performance of a Curtiss propeller with four 838-1C2-1SR1 blades on a YP-47M airplane at high blade loadings and engine powers. The study was made for a range of power coefficients between 0.30 and 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio, inasmuch as corrections for the effects of tunnel-wall constriction on the installation have not been applied" (p. 1).

Report presenting an investigation of the aerodynamic characteristics of a model of the NACA RM-10 in the hypersonic tunnel at a Mach number of 6.9. Longitudinal pressure surveys were made on the body without fins at zero lift and at angles of attack. Results regarding the pressure distributions, forebody pressure forces, body forces, fin-body combination forces, pitching moment and center of pressure, variation of the zero-lift drag components with Reynolds number and Mach number, variation of the lift-curve slope and center of pressure with Mach number, and Schileren observations are provided.

Four strut-supported, transpiration-cooled turbine blades were investigated experimentally in a turbojet engine. The blade shells were fabricated by the mold-sintering method with spherical stainless-steel powder. Two blades were investigated in order to evolve suitable capping methods for the blade tip. Two other blades were used to evaluate the durability of the porous-shell material. The blades were investigated at a turbine-tip speed of 1305 feet per second, an average turbine-inlet temperature of about 1670 F, and at a porous-shell temperature limited to a maximum of approximately 1040 F.

The damping in yaw and the directional stability of a model freely oscillating in yaw were measured tail-off and tail-on and compared with the values obtained by theoretical consideration of the unsteady lift associated with an oscillating vertical tail. A range of low frequencies comparable to those of the lateral motions of airplanes was covered. The analysis includes the effects of vertical-tail aspect ratio and the two-dimensional effects of compressibility.

Investigating possible structural, mineralogical and volcanic relations between the central core and ore-producing sediments of the northeast flank.

Test work on two samples of high-grade Rand uranium precipitate indicated the desirability of calcining it at 400' to 500'C. to cut shipping costs and provide a refinery feed quite amenable to treatment by the nitric acid digestion-TBP process.