The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area exhaust-nozzle operation, the primary effect of the radial inlet-air-flow distortions was to reduce the engine air flow, and the primary effect of the circumferential distortion was to impose a temperature profile on the turbine, both resulting in reduction of thrust.

Report presenting an investigation at sea-level static conditions to determine the effects of radial discharge of cooling air from turbine rotor blades on turbine performance in two turbojet engines, one with a centrifugal compressor and the other with an axial-flow compressor. Results regarding the performance characteristics, efficiency comparisons, and some interpretation are provided.

Report presenting measurements of the normal force and pitching moment of a rectangular tail surface at Mach 1.9 to determine the interference effects due to trailing shock waves from an axisymmetric body with a jet exiting from a sonic nozzle in the base. The data were obtained at various jet pressure ratios and locations of tail with respect to the body. Results regarding tail location, tail pitching moment, and tail-shock-wave effects on base pressure are provided.

Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.

"Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).

Theoretical calculations of specific impulse to determine the separate effects of increasing the combustion-chamber pressure and the nozzle expansion ratio on the performance of the propellants, hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine and AN-F-58 fuel - white fuming nitric acid (95 percent). The results indicate that an increase in specific impulse obtainable with an increase in combustion-chamber pressure is almost entirely caused by the increased expansion ratio through the nozzle.

Report presenting several short two-dimensional subsonic diffusers over a range of throat Mach numbers from 0.3 to 0.9. The designs incorporated an effective diffusion angle of approximately 30 degrees and an area ratio of 3. At a throat Mach number of 0.7, the resulting profile distortion of the unmodified 30 degree diffuser was diminished from about 11 to approximately 4 percent by using any of the configurations.

From introduction: "The work described here was part of an integrated investigation of the fundamental properties of uranium oxides done for the Mallinckrodt Chemical Works. Electrical measurements were employed to characterize the oxides produced by various processes from different starting materials. The basic objective of the program was to determine those factors which affect the sintering characteristics of uranium dioxide."

A method is described whereby many types of flaws lying close to the surface of a metal can be ultrasonically detected, regardless of the time duration of the interrogating pulses. Lamb waves are established in the metal between a flaw and the surface by an ultrasonic beam which impinges at the proper angle of incidence. A suitably positioned receiver transducer picks up the waves to reveal the flaw. In this method the usually troublesome surface echo is eliminated from the receiver by an acoustic barrier, making it well suited for routine and automatic testing. Results of applying the technique to several testing problems are discussed.

It has been suggested by many workers in the power reactor field that a more efficient utilization of natural uranium may be obtained in thermal reactors if the Pu produced in a fuel cycle were used to enrich a subsequent cycle in which the irradiation-depleted-uranium would be reirradiated. The work described here was done for the purpose of evaluating the reactivity value of the Pu enrichment under the assumption that all plutonium produced is, after chemical separation, fabricated into separate fuel elements and not alloyed with recycled uranium. It has been suggested that the reactivity value of the Pu decreases with exposure to such an extent that highly burned plutonium should be discarded. We, therefore, wish to look at two of the variables affecting the limiting exposure: the reactivity value of the fuel as a function of exposure and temperature and the fraction of potential fissions which would be discarded as a function of exposure. Though the residence time of the Pu fuel before reprocessing, refabrication, and recycling depends upon the relative decrease in specific power, decrease in reactivity due to fission product build-up, the lifetime of the fuel elements before failure, and the cost of reprocessing, only the first …

Neutron attenuation in the old pile shields is dependent more and more on the slowing down characteristics of the iron as the hydrogen is baked out of the masonite. For neutrons above 1 or 2 Mev, iron does a good job by inelastic scattering. However, below this energy attenuation can be done only by the gradual moderation by elastic scattering to thermal energies with subsequent capture in the iron. Since iron is heavy and thus a poor moderator, there is a good possibility that many neutrons of intermediate energy will leak out of a burned out shield. Also, iron has a large dip in its cross section at 25 Kev which might allow a large burst of neutrons at this energy to leak out. Measurements using a lucite moderator with gold foil detectors indicate a large leakage of neutrons of intermediate energy, but interpretation of these measurements is difficult. These considerations prompted an attempt to get a rough idea of the energy distribution of the leakage neutrons through pure iron using a simple qualitative theory.

Average coefficients of thermal expansion of the temperature range 25 C to approximately 425 C are reported for numerous types of graphite. The dependence of thermal expansion on crystal orientation and crystallite size and the effects of oxidation and cold test hole irradiation are discussed. An empirical relationship between thermal expansion and the initial rate of physical expansion under cold test hole irradiation is formulated.

We have recently completed measurement of resonance escape probability in the BNL reactor and in several slightly-enriched uranium light water moderated lattices. In addition, WAPD has made available to us data from other slightly enriched uranium-water lattices, so that about 18 lattices in all have been done.

From Abstract: "This report covers the preliminary literature survey and the screening of activated cesium iodide and several alkali halides to qualitatively determine their luminerscence. The report also includes a proposal of the future work and a proposed budget for the 1957 fiscal year."

Evaluation of the conditions under which the interaction effects of two or more sub-critical quantities of enriched uranium may be safely arranged.

From Introduction: "This report presents the cooling-air requirements of a "paper" air-cooled turbojet engine operating over a wide range of flight Mach numbers and altitudes. The results are presented for a two-stage-turbine turbo-jet engine having a turbine-inlet temperature of 2500^o R and operating at sea-level static conditions and flight Mach numbers from 0.90 to 2.5 and flight altitudes from 40,000 to 70,000 feet. In addition, the effect of decreasing the blade-inlet cooling-air temperature on the required coolant-flow ratio is presented."

Report presenting tests to determine the flight characteristics of an F-86 airplane equipped with a blowing-type boundary-layer-control installation on the trailing-edge flaps. The effectiveness of the flap was determined in conjunction with slatted leading edges and an inflatable rubber boot on the leading edge. Measurements were made of lift, drag, flow requirements, and computations for take-off, climb, and landing.

"Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslip as the vertical tail" (p. 1).

"The theoretical performance of pentaborane has been recalculated using recent data on the vapor pressure of boric oxide. Previous calculations were based upon vapor-pressure data obtained some years ago by a method not as accurate as that employed in current investigations. The recalculated performance data for pentaborane differ appreciably from previously published data and are considered more accurate for evaluation of the relative potentialities of boron-containing fuels" (p. 1).

Report presenting an experimental investigation to evaluate combinations of fuselage and inlet throat boundary-layer removal for a ramp-type side inlet in the 8- by 6-foot supersonic wind tunnel at Mach numbers 1.5, 1.8, and 2.0. Optimum combinations of fuselage and inlet throat boundary-layer removal showed gains in available thrust from 3 to 10 percent over the case of no inlet throat bleed. Results regarding variations of diffuser total-pressure distortion, recovery and external drag coefficients, and net gains in available thrust are provided.

Report presenting an investigation to determine the effects of external ribs, or load carrying fences, on the rolling effectiveness and drag on swept wings of two different stiffnesses. The primary effect of adding fences was a decrease in torsional flexibility and an increase in zero-lift rolling effectiveness. The aerodynamic effects on zero-lift rolling effectiveness due to adding fences are negligible.

From Introduction: "The purpose of this report is to further analyze the turbine performance results of reference 1 with the objective of isolating the contribution of the cooling air to the turbine performance and establishing some systematic relation between these cooling-air effects and the turbine operational parameters."

Report presenting the design details of two transpiration-cooled strut-supported turbine rotor blades. One design uses a sintered blade shell while the other uses a wire blade shell. Ideal coolant flows were found for an effective gas temperature of 1425 degrees Fahrenheit, a coolant temperature of 180 degrees Fahrenheit, and a shell temperature of 600 degrees Fahrenheit.

Report presenting testing of two airplanes, the F6F-3 and F-86A, fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics and flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. Results regarding the aerodynamic characteristics and pilot opinions for each plane are provided.