Report presenting a control-motion study program with a Republic F-84F using a cross section of tactical maneuvers performed during squadron operational training. Time-history figures, airspeed and Mach number envelopes, and other aerodynamic characteristics are provided.

A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.

Report presenting a flight-test program investigating a modification to an interceptor system. Results indicate that a significant improvement in the overall response characteristics of the system. The modification minimizes the interaction between the antenna and interceptor motions, which can have a serious influence on flight path stability during a lead-collision attack.

During the development of in-reactor corrosion experiments three types of bomb designs have been developed for following quantitatively the consumption of oxygen in a bomb which is fabricated from the particular metal under test. The bombs are designed so as to be rocked continuously during their in-reactor exposure, consequently agitating the uranium salt solution contained in the bomb and permitting gentle movement of the solution past metal specimens and other corroding surfaces. The oxygen pressure is produced within the bomb at the beginning of the run either by the withdrawal of gas from an oxygen tank or by the decomposition of hydrogen peroxide added just prior to closure. Temperature measurements are obtained by mans of thermocouples placed in a well within the bomb body or, in the latest design, there will also be thermocouples staked at several points on the outer wall of the bomb. The assembly is inserted in an experimental access hole in the reactor, brought up to a predetermined operating temperature by means of an electric furnace in close contact with the bomb, and allowed to remain for the desired amount of exposure to reactor radiation. Periodic measurements of temperature and pressure are made and the bomb …

Report presenting an evaluation of a 1/4-sector of an annular combustor designed for use with pentaborane fuel at a simulated altitude condition. Results regarding the pentaborane performance, combustor development, and the JP-5 fuel performance are provided.

The operation of the HRT mockup was on 0.042m UO2SO4, 0.024m H2SO4, and 0.005m CuSO4 at 280 C and 1400 psi pressure. with the O2 content at near 500 ppm. The pump showed bearing wear and high corrosion. The letdown heat exchanger was removed from the mockup and sectioned. The metallographic examination revealed corrosion. Results of corrosion runs on Ti, zircaloy-2, and stainless steel are given.

A qualitative theory for cake formation in ThO2 slurries is presented. The sphere formation which occurs in "Standard" slurry can be explained on the same basis. The irregular and unpredictable yield strength is easily fitted into the theory. On the basis of this theory, the writer has been led to the conclusion that only colloidally stable slurries, or slurries with crystallites or comminution-resistant particles which are large enough to overcome colloidal effects (probably larger than 0.1u) can be used with assurance in the ThO2 reactor system. This conclusion holds for 300 gm/kg slurries as well as for more concentrated mixtures.

In analyzing stresses, deflections, and forces in piping and certain structural systems, it is useful to have a set of equations giving the deflections at any point of a curved beam in terms of the various loads acting on the beam. This technical report presents the deflection equations for a curved circular-arc beam of variable length. The cases treated include in-plane and out-of-plane bending due to forces and moments applied to the end of the beam in three principal directions, and uniformly distributed loads applied along the beam in these three directions. Deflections were calculated by the strain energy method using Castigliano's theorem.

Report presenting testing of a transonic compressor rotor with double-circular-arc blade sections and inlet guide vanes turning counter to the direction of rotor whirl to determine the effect of blade-row interaction on the performance of a transonic rotor. Results regarding overall performance, guide-vane performance, rotor-inlet conditions, rotor-outlet conditions, consideration of radial equilibrium, blade-element performance, and axial asymmetry in rotor-outlet flow are provided.

Report presenting flight tests on an FJ-3 airplane to determine the flight characteristics of a carrier-type airplane with area-suction and blowing boundary-layer control on the trailing-edge flaps. Measurements were made of lift, drag, and bleed-air requirements for the different types of boundary-layer control systems. Results regarding lift, drag, flow requirements, performance, pilots' opinions, and approach-speed criteria are provided.

Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.

Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.

Report issued by the Oak Ridge National Laboratory discussing quarterly progress of the Homogeneous Reactor Project. Progress of operations, design, development, and analysis is presented. This report includes tables, illustrations, and photographs.

Memorandum presenting an investigation of the static longitudinal stability characteristics of two wings of different construction and slightly different flexibilities in the 16-foot transonic tunnel. The wings had the same external dimensions but one had a steel construction and the other was made of plastic reinforced by a steel core.

Memorandum presenting a general wave equation derived governing the propagation of sound in a stratified moving medium, the velocity of which varies only along one coordinate. A simplified equation is adopted which is satisfactory for the present application.

A report discussing a geologic reconnaissance of the Capitol Reef area, undertaken to evaluate the uranium deposits and determine their geologic characteristics.

"This is a bibliography of journal articles relating to beryllium oxide. Sources consulted include; Chemical Abstracts, 1951-1955; Physics Abstracts, 1951-1955; Industrial Arts Index, 1955-Jan, 1957; and the library card catalog. Starred articles are available in the library.

In order to test the effect of chromate ion on the corrosion of Zircaloy-2 a 0.04 m uranyl sulfate solution (enriched) containing added acid, copper sulfate and 557 ppm Cr (VI) was autoclaved with rocking at 280 C for about eight days in the HB-5 facility of the LITR. The average corrosion rate established by the a rate of consumption of oxygen was 9.9 mpy at a power density of 4.9 w/ml. It is indicated by comparison with a previous corrosion study under LITR radiation that the presence of Cr (VI) had no significant effect on the radiation corrosion of Zircaloy-2 by enriched uranyl sulfate solutions. However, the data are not conclusive and may be interpreted as showing a low corrosion rate for a limited period (i.e. a short term inhibition) followed by a correspondingly rapid corrosion.

In order to test the effect of chromate ion on the corrosion of Zircaloy-2, a 0.04 m uranyl sulfate solution (enriched) containing added acid, copper sulfate and 557 ppm of Cr (VI) was autoclaved with rocking at 280 degrees C for about eight days in the HB-5 facility of the LITR. The average corrosion rate established by the rate of consumption of oxygen was 9.9 mpy at a power density of 4.9 w/ml. It is indicated by comparison with a previous corrosion study under LITR radiation that the presence of Cr (VI) had no significant effect on the radiation corrosion of Zircaloy-2 by enriched uranyl sulfate solutions. However, the data are not conclusive and may be interpreted as showing a low corrosion rate for a limited period (i.e. a short term inhibition) followed by correspondingly rapid corrosion.

Study carried out to determine a suitable reactor system or systems for the testing of water, gas, and liquid-metal cooled fuel assemblies.

"Drag characteristics of a series of related conical and circular-arc afterbodies are presented for Mach numbers from 0.6 to 1.3. Drag was obtained from pressure measurements on the boattail and solid base. The boattail angles tested ranged from 0 degrees to 45 degrees for ratios of base diameter to maximum body diameter ranging from 0 to 1.0" (p. 1).

"A number of noise-suppression nozzles were tested on full-scale engines. In general, these nozzles achieved noise reduction by the mixing interference of adjacent jets, that is, by using multiple-slot-nozzles. Several of the nozzles achieved reductions in sound power of approximately 5 decibels (nearly 70 percent) with small thrust losses (approx. 1 percent). The maximum sound-pressure level was reduced by as much as 18 decibels in particular frequency bands" (p. 1249).

A prototype sampler for obtaining samples of high radioactive UO2SO4 solution for use in the HRT is presented. It was successfully operated in conjunction with a low pressure water system and a high pressure, high temperature UO2SO4 system.

Tests were performed in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability and control characteristics of a 1/20-scale model of the McDonnell F4H-1 airplane at Mach numbers of 1 57, 1 87, 2.16, and 2.53. This is the second phase in a series of tests performed on this model. The Reynolds numbers for these tests, based on the mean aerodynamic chord of the wing, are 1.446 x 10 (exp 6), 1.269 x 10 (exp 6), 1.116 x 10 (exp 6), and 0.714 x 10 (exp 6) at Mach numbers of 1.57, 1.87, 2.16, and 2.53, respectively.