From introduction: "Revision of skunk genus Spilogale based upon a study of about 380 skins with skulls and 75 additional skulls from the collection of the Biological Survey."

Report presents the results of tests made of a Clark y airfoil with a Clark y Fowler flap and of an NACA 23012 airfoil with NACA Fowler flaps. Some of the tests were made in the 7 by 10-foot wind tunnel and others in the 5-foot vertical wind tunnel. The pressures were measured on the upper and lower surfaces at one chord section both on the main airfoils and on the flaps for several angles of attack with the flaps located at the maximum-lift settings.

A model for the capture spectrum of uranium is introduced in which levels occur at 7, 30, 30+D, 30+2D, ..., ev. Gamma ray and neutron widths are derived from the experimental data for values of D between 10 and 25 ev. The constants of the 7 volt level prove to be independent of D. Extrapolation, using the one level formula, gives a capture cross section at (1/40) ev of 4.9 x 10(24) cm2; this number is, however, quite sensitive to the value taken for the resonance activation. Both neutron and gamma ray widths for the higher levels are approximately proportional to D.

Equations are presented for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of a satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling or in flight at low airspeeds, and to prevent flutter. Examples are presented to show the design features of spring tabs required to solve these problems for airplanes of various sizes.

Report discussing experiments to "determine the empirical relation, if any, between the nitrogen, carbon, and density of recast uranium metal."

From Introduction: "The purpose of the present paper is to present results obtained recently relating to the characteristics of a full-span sharp-edge spoiler with an 0.02-chord projection above the wing surface at several chordwise positions and also to the relative effectiveness of the sharp-edge spoiler and a wedge-type spoiler located at the 80-percent-chord line."

From Introduction: "An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of an axial-flow-compressor type turbojet engine with a two-stage turbine is presented herein. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel (references 1 and 2). The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine."

Report presenting a flight investigation on a rectangular ram jet over a range of fuel air ratios, combustion chamber inlet velocities, and pressure altitudes. A comparative study to determine the effects of altitude, combustion-chamber-inlet velocity, and fuel-air ratio on starting characteristics, minimum blow-out limits, combustion efficiency, gas total-temperature ratio, and net-thrust coefficient for three flame holders was also conducted.

Report presenting the results of an investigation on a rectangular ram jet to determine the effect of variation in fuel pressure on the starting characteristics, minimum blow-out limits, combustion efficiencies, gas total-temperature ratio, and net-thrust coefficient. Testing occurred using three different fuel nozzles and over a range of pressure altitudes, airspeeds, and fuel-air ratios.

Report presenting a study of the effects of air velocity on the energy and power of the spark in a constant ignition source and the duration of the spark discharge in the spark gap for various conditions of electrode spacing, electrode diameter, air temperature, and pressure. Energy and average power increased with pressure, velocity, and electrode spacing and electrode diameter and air temperature had negligible effect.

From introduction: "The test was performed to gain knowledge which would be useful for evaluating and improving currently planned methods for the design and construction of high density concrete shielding."

A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircraft research station at Wallops Island, Va. The results include the longitudinal stability derivatives, control effectiveness, drag characteristics, and control-surface hinge-moment characteristics for a Mach number range of 0.7 to 1.45.

Report presenting the use of a simplified method of analysis in order to estimate the turbine blade-tip speed required to design satisfactory two-stage turbines. The investigation allows for certain conditions for optimal two-stage turbine design to be determined.

Report presenting an investigation of the overall performance characteristics of a complete canard-type missile configuration with wing-mounted nacelle engines in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers. The investigation covered a range of angles of attack, control-surface-deflection angles, and engine mass-flow ratios. Results regarding the overall force and moment evaluation, effect of engines on configuration performance, and effect of variation of engine mass-flow ratio on configuration and inlet performance are provided.

Report presenting an investigation to evaluate two methods of decreasing losses of unevaporated fuel from the combustion zone of turbojet-engine combustors. One method had fuel dams on the inner surface of the combustor liner and one had a ceramic coating on the combustor-liner walls. Results regarding the effect of the fuel dams, effect of ceramic coatings, effect of combination of fuel dams and ceramic coatings, and effect of ceramic coating on carbon deposition are provided.

The proton beam in the Cosmotron is accelerated to an energy of 2.3 billion electron volts by a radio frequency voltage which is impressed across an insulated gap in the ferrite loaded accelerating cavity of the vacuum chamber. To maintain a constant orbit radius as the beam is accelerated, the frequency of the accelerating voltage must increase from the initial value of 370 kc/sec to 4200 kc/sec during the one second magnet pulse. Over the entire 11:1 frequency range, a minimum gap voltage of 2000 volts rms must be maintained. At every instant throughout the magnet pulse, the frequency of this voltage must be a predetermined function of the magnet field to a high degree of accuracy. Frequency errors greater than about .2 percent result in loss of beam due to excessive radius changes. Smaller errors than this however, can excite fatal phase oscillations in the beam if they occur rapidly. As little as .005 percent frequency modulation can result in total beam loss if it occurs at a rate of several kc/sec, where the beam is most sensitive to such disturbances.

Report presenting an investigation of a 45 degree sweptback-wing model with interchangeable round and sharp leading edges to determine the effect of leading-edge separation on the loads experienced by the models in gusts. Leading-edge separation was found to increase the gust load, which appeared to vary based on the gust-gradient distance and velocity.

Memorandum presenting an investigation of the performance characteristics of a double-shroud ejector for the purpose of evaluating its effectiveness as an exit nozzle. Calculations based on ejector performance data, taken with the ejector discharging into quiescent air, indicate that thrust performance on the order of ideal nozzle thrust may be obtained over a Mach number range of 0.8 to 2.3 from a double-shroud ejector. The results of a simplified theoretical analysis are in fair agreement with those experimentally obtained.

The vapor pressure of nickel carbonyl was determined with material obtained by laboratory preparation with CO and Ni powder and by purifying commercial nickel carbonyl. The observed vapor pressure data were used in the derivation of the following equations which express the vapor pressure, P, of liquid nickel carbonyl and the sublimation pressure, P/sub s/, of the solid, respectively, as a function of the absolute temperature, T: log P = 7.88431578/T and log P/sub s/ 10.1897-2173/T. The average heat of vaporization is calculated to be 7.22 plus or minus 0.01 kcal per mole and the molecular heat of sublimation of Ni(CO)/sub 4/ is 9.94 plus or minus 0.11 kcal. Extrapolation to 760 mm Hg gives a boiling point of 42.2 deg C. The melting point of purified nickel carbonyl occurred at -17.2 deg C. The sensitivity of the melting point to the effect of impurities was demonstrated with commercial nickel carbonyl which melted at-19.4 deg C before purification, at --18.3 deg C after distillations at 0 deg C, and at -17.2 deg C after sublimation at -25 deg C. The vapor pressure of liquid nickel carbonyl at 0 deg C is of little value in evaluation of the purity of …

Report presenting an investigation in the free-spinning tunnel to determine the effect of lateral-control systems using various combinations of spoilers, slots, and deflectors as compared with ailerons on the spin-recovery characteristics of a model of a 35 degree swept-wing fighter loaded heavily along the fuselage. Testing indicated that the ailerons were favorable for recovery when they were deflected full with the spin. Results regarding the effect of ailerons and two spoiler-slot-deflector configurations are provided.

"The effects of some rivets, butt joints, and lap joints on the drag of a body of revolution at zero lift at supersonic Mach numbers to 2.1 have been obtained in free flight with rocket-propelled models. The butt joints tested showed no significant effects on the drag. Rivets and lap joints increased the drag of the smooth-body configuration, the forward-facing lap joints contributing the greatest increases" (p. 1).

Abstract: "The results of the investigation of three methods of obtaining transverse stability in linear accelerators for ions are presented and discussed. For electric or magnetic quadrupole focusing the range of stable operation, oscillation amplitudes, and the operation of an actual grid is analyzed from measurements of the field distribution. Finally, the formulas applicable to focusing by axial magnetic lenses are presented."

Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distributions in sideslip at six span stations on a 45 degree sweptback, untapered, vertical tail with a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span.

Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.