Annual report of the Liquid Metal Fuel Reactor Experiment describing progress during calendar year 1958 and as well as an evaluation of progress and plans for future work.

Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.

Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stability was becoming marginal at high angles of attack at Mach number 3.5.

Several compatibility test of various materials in contact in sodium under 500 psi pressure were conducted for 716 hr at 1500 F. Of the diffusion couples studies, the Inconel-beryllium system showed the largest amount al alloying. The reaction between molybdenum and beryllium resulted in the formation of two compounds, both of which were severely cracked in several areas. The molybdenum-INOR #8, and the INOR #8p type 316 stainless steel interfaces showed little if any alloying.

Report presenting an experimental investigation of a submerged air inlet incorporating a cascade of airfoils for turning and diffusing the entering air. Variables associated with submerged air inlets and airfoil-cascade designs were considered, including changes to the ramp plan form and angle for the submerged inlet and the cascade-axis inclination, cascade-blade angle, solidity, and inclination of the center line of the duct for the cascade.

The probabilities for nine electronic transitions among the low lying excited states in the C2 molecule are calculated by the dipole moment operator method and are given in the form of oscillator strength (or f values).

Report presenting a rocket-propelled missile model with cruciform, triangular, inline wings and tails, which has been tested through a range of Mach numbers at small wing-deflection angles. Results regarding the stability and damping, control effectiveness, and hinge moments are provided.

Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio.

From introduction: "The objective of this report is to present the results and describe the tests of both the 2-in. D and 6-in. D contractors using mill pulp feeds. Work on determining resign attrition is also reported. ORNL-CF-52-12-101 described the results of preliminary tests using synthetic ore pulps."

Report presenting the effects of nacelle location on the zero-lift drag of 45 degree sweptback wing-body combinations with boattail and cylindrical afterbodies at a range of Mach and Reynolds numbers. The nacelles were located at three different areas and the afterbody shape was also altered by replacing the boattail afterbody with a cylinder. Results regarding faired curves of the variations of total drag, base drag, and fin drag coefficients, and applicability of the transonic area rule are provided.

Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane were conducted to determine the distribution of pressure over the external wing fuel tank installation and over the vee tail and ventral fin. The data were obtained for a range of angles of attack and sideslip and elerudder deflection angles; the presentation is in tabular form.

An accurate determination of the parameters of the resonance excited by the interaction of the 132 eV neutrons with the Co 59 target nucleus has been made, using the fast choppers at Brookhaven National Laboratory in the United States and Chalk River Laboratory in Canada. Neutron transmission through thick and thin samples resulted in the following parameters: [parameters not transcribed]. In addition, measurements of the resonance capture γ-ray intensity gave the value for the radiation width Γγ= 0.40 ± 0.04 eV, based on the known thermal capture cross section of cobalt of 37.5 barns. The reduced and total resonance capture integrals are calculated from the above parameters to be 50.5 ± 5.5 and 67.0 ± 5.5 barns, respectively. The above results are compared with previously determined resonance parameters and also with direct measurements of the total resonance capture integral.

From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."

Report presenting an investigation in the transonic blowdown tunnel between Mach numbers of 0.65 and 1.4 to determine whether the principles of the transonic area rule could be used to improve the transonic drag-rise characteristics of a semielliptical shaped sweptback air inlet installed in the root of a sweptback wing-body combination. Results regarding the effect of the inlet and the interaction of Mach number and drag coefficient are provided.

This report is a summary of the neutron attenuation data which have been obtained at the Brookhaven shielding facility on a mock-up of the fuel-rod-unloading plug used in the KAPL Reactor. Before this program was initiated, a number of small scale tests had been made in the ORNL lid tank on carbon steel mock-ups of components of the rotating plug. The results of the tests indicated considerable neutron streaming through the vertical steel and air members of the plug. However, the lid tank source strength and dimensions did not permit the tests to be extended to the full plug height. In view of the concern aroused by the ORNL tests and the absence of fundamental information on the transmission of neutrons through steel and the addition height (12') available here resulted in a request for BNL to construct and test a mock-up of a sector of the SIR top plug in accordance with KAPL specifications.

From abstract: "This report summarizes the corrosion data obtained for nine construction materials located throughout the ORNL Purex Pilot Plant Acid Recovery Unit during seven hundred hours of operation."

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."

Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.

Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.

Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.

Report presenting results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model for a Mach number of 2.01. Normal-force, lateral-force, pitching-moment, and yawing-moment coefficients of the airplane model were measured, and schileren photographs of the various configurations were obtained.

Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.

Introduction: "The problem of determining the properties and necessary controls on the TBP Plant waste disposal to eliminate transport line plugging and to permit higher concentration prior to return of this to the tank farms was studied. A report of preliminary findings was made to L. W. Finsh on January 31, 1953. This report compiles information in the aforementioned report and findings since its issuance. Previous studies related to this problem are summarized in the U. R. Technical Manual, HW-19140."

Abstract: "The trajectory analysis of an immobilized plasma has been generalized to include the presence of electrons having a far similar radius of gyration and, therefore, fitting readily into the broader scale structure established by the ions. This problem has been adapted to machine calculations and the results for various strengths plasmas have been calculated."