This report gives the results in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics on the interference drag and propulsive efficiency of a nacelle-propeller combination located in 21 positions with reference to a thick wing. The lift, drag, and propulsive efficiency were obtained at several angles of attack for each of the 21 locations. A net efficiency was derived for determining the over-all effectiveness of each nacelle location. Best results were obtained with the propeller about 25 per cent of the chord directly ahead of the leading edge. A location immediately above or below the wing near the leading edge was very poor.

Report discussing vibration experiments on a model of the Grumman F6F at up to 500 miles per hour. There was no indication of actual flutter by shift or frequencies or by decreasing dampening. The symmetrical and unsymmetrical bending frequencies and responses are provided.

From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel to determine the lift, drag, pitching-moment and stalling characteristics of a 1/4 -scale partial-span model of the left wing of the Republic XF-12 airplane. The effects of a duct inlet, located between the nacelles at the leading edge of the wing, on those characteristics were also investigated. The Reynolds numbers for the investigation covered a range from 4,500,000 to 8,600,000. The results of the investigation indicated that maximum lift coefficients of 1.36, 1.71, and 2.11 were measured on the model with flaps neutral and deflected 20 deg and 55 deg, respectively at a Reynolds number of 8,600,000."

Abstract: The effect of temperature upon the rate of reduction of uranium trioxide by ethyl alcohol has been investigated, and a comparison of the reactivity of the dioxide produced at various temperatures has been made. The percent of carbon in the end product has been studied with respect to both temperature of reduction and length of exposure to alcohol. Optimum conditions for the reduction have been suggested.

Report presenting an investigation of pressure distributions and flow characteristics at low speed through a range of yaw and angle of attack through the stall for three small-scale low-aspect-ratio pointed wings with varying degrees of trailing-edge sweep. An effort was made to correlate pressure distributions with the strong conical vortex flow observed. Results regarding chordwise pressure distributions and flow characteristics, section lift characteristics at zero yaw, spanwise-load distributions, centers of pressure at zero yaw, and wing force and moment characteristics are provided.

"An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. An analysis of the performance of the rotor was made based on detailed flow measurements behind the rotor. The compressor apparently did not obtain the design normal-shock configuration in this investigation. A large redistribution of mass occurred toward the root of the rotor over the entire speed range; this condition was so acute at design speed that the tip sections were completely inoperative" (p. 1).

Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.

The results of this study are tabulated in Summary Tables A and B below. For the most part, these values were read from smoothed curves drawn thru the plotted experimental data. The values for aluminum (i.e., 0 w/o Li) were taken from the 1948 Edition of the ASM Metals Handbook. The room temperature properties are reported for lithium contents of 0, 3.5, 7 and 10 weight per cent. In the case of the high temperature properties, there were insufficient data to allow extrapolation and interpolation to pre-chosen compositions: these properties are therefore reported only for the compositions of the actual samples.

A number of pipetting aids are commercially available which obviate the necessity of filling pipets by oral suction. Most of the commercially available devices involve fitting the pipet into a soft tight fitting bushing and filling by means of either a piston or a rubber bulb. The pipet is then emptied by means of a valve control which permits, it is claimed, a dispensing accuracy of 0.1mL. It is at once apparent that the probable error (10% for a 1 mL. pipet) is considerably greater than is permissible for great precision. In practice these devices are found to be awkward and after a period of use tend to become even more so due to corrosion of the valve and aging of the rubber bushing and rubber bulbs.

The field of mathematics which deals with the construction of charts representing mathematical laws is known as Nomography. Often it is necessary to repeatedly solve mathematical formulae, but with different values for the symbols involved. The manipulation of the formulae, or repeated constructions of graphs, may require considerable work, as well as carry with it the possibility of errors invalidating the results. In such a situation, the construction of a single chart which would serve for all the solutions would obviously be of considerable value.

Report discussing a flight test of a four-nacelle delta-wing airplane configuration based on the transonic area rule in order to counteract the effects of high pressure drag at transonic and supersonic speeds. The testing verified that the transonic area rule can make designing complex aircraft with low transonic and supersonic pressure drag much easier.

Memorandum presenting a procedure based on the transonic area rule, which has been used to design a four-nacelle delta-wing airplane configuration. A flight test of a model of the configuration showed a zero-lift transonic drag rise of 0.010 which, when compared with estimates, indicated the absence of adverse interference effects.

In connection with different seals for C & D equipment it appears advantageous that many parts could be made of rubber or other elastic polymers. However, data on the deterioration rate of these materials under irradiation are somewhat scant in the available literature. It appears that for neutrons and pure gamma radiation that a good grade of natural rubber stands up best in all the test reported and because the results of the neutron irradiation are so closely correlated with results from gamma it has been proposed that the principal source of damage is caused by secondary irradiation generated within the rubber by the neutrons.

From Summary: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect of freeing the controls."

"The drag of bodies has now assumed greater importance because, as shown in NACA RM L53I15a, 1953 and NACA RM A53H18a, 1953, the transonic drag rise of an airplane can be the same as its equivalent body. Obviously, the airplane designer would like his airplane to have a low-drag equivalent body. This paper shows some of the factors which minimize the drag of bodies at transonic and supersonic speeds and shows some of the penalties caused by deviating from low-drag body shapes" (p. 1).

From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some details and is therefore not included herein."

Nuclear physics research with 22-Mev protons in the 86-in. cyclotron included angular-distribution measurements of neutrons from (p,n) reactions in nine target elements; measurement of the angular distribution of fission fragments from proton-induced fission of U233, U225, U228, Th230, and Th232; measurement of alpha-particle angular distributions from (p,α) reactions a study of the neutron-deficient isotopes of terbium and completion of an extensive program of the measurement of activation cross sections. Two more targets for cyclotron production of isotopes were developed, and the production yields for 14 radioisotopes are summarized. A new record for continuous beam power on a production target, 36 kw for 5 hr, was achieved. The design of a beam-deflector system for the 86-in. cyclotron has been completed, and several of the components have been fabricated ; a shutdown for installation is scheduled for October 8. The deflected N+++ beam of the 63-in. cyclotron was used in a study of the gain and loss of electrons by nitrogen lens passing through thin foils, and the equilibrium charge distribution of lens as a function of energy was thus obtained. The excitation functions were measured for nitrogen-induced reactions on both nitrogen and oxygen. Assembly restrictions of the prepared 114-in. heavy-particle cyclotron …

Report presenting a paper to consider the feasibility of attaining, through the use of non-afterburning engines, essentially the same range with an all-supersonic mission as the range currently obtained with a mission incorporating subsonic cruise and supersonic dash.

Report presenting an investigation to determine the effects of inlet flow distortion on the compressor stall and engine acceleration characteristics of a J65-B-3 turbojet engine. A sinusoidal circumferential distortion and two abrupt radial tip flow distortions were introduced at the engine inlet at several altitudes and Mach number 0.8. Results regarding the definition of inlet flow distortions, acceleration limits, compressor pressure ratio at stall, fuel flow for stall, and maximum acceleration rate are provided.

Report presenting wind-tunnel testing to determine the effect of leading-edge sweepback on the lift, drag, and pitching-moment characteristics of 3-percent-thick wings of aspect ratio 3 and taper ratio 0.4. Increasing the leading-edge sweepback of wings decreased both the lift-curve slope and the variation of static longitudinal stability at zero lift with Mach number. Results regarding lift, pitching moment, and drag are provided.

The action of a surge control that reduced fuel flow after receiving an indication of surge initiation was investigated. The control system could successfully limit surge to only 1 cycle but could not completely eliminate surge. Inability to interrupt a surge cycle before its completion was attributed to the conclusion that a surge cycle is irreversible.

An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics …

From Summary: "The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach numbers of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied."

From abstract: "This report contains a summary of the latest improvements in zirconium purification as developed by the Y-12 research, pilot plant, production, and engineering groups, all of whom have been generously cooperating in this project."