The countercurrent gas-liquid system BF3(g)—anisole·BF3(l) for the concentration of boron isotopes has been studied. The single-storage separation factor varies from 1.039 at 0°C to 1.029 at 30°C. Rate of exchange is rapid, and, with efficient contacting equipment, complete exchange may be obtained in less than 15 sec. A total separation of 1.525 has been realized in laboratory equipment. The critical-product reflux reaction is quite efficient. Only about 55 moles of BF3 remain in each million moles of effluent solvent under laboratory conditions. The vapor pressure of BF3 over the complex rises sharply as the temperature is increased. At 0°C the pressure is 150 mm Hg, and at 40°C the pressure has risen to 1800 mm Hg. From vapor-pressure measurements, an approximate upper limit of ΔH= -12kcal per mole of complex was calculated for the reaction [equation not transcribed]. Qualitative tests indicate good resistance of anisole to decomposition by BF3 under plant conditions. The uncatalyzed exchange of boron between BF3 and BCl3 was found to be too slow to be exploited in a countercurrent system. The single-stage, equilibrium separation factor for the Nitrox system is a function of acid concentration. At 26°C the factor ranges from 1.064 with 1 M acid …

Report presenting one-tenth-scale models of two inlet configurations of fighter-type aircraft have been tested in the 4- by 4-foot supersonic pressure tunnel. The pressure-recovery and force characteristics of the inlets were determined as a function of mass-flow ratio, angle of inlet compression, angle of attack, and Mach number.

Report presenting free-oscillation tests to determine the dynamic hinge-moment characteristics of a trailing-edge flap-type control surface on a 4-percent-thick unswept wing with low aspect ratio. Tests were made over a range of Mach numbers, reduced frequencies, and low test speeds. Results regarding the effects of wing motion, damping moment and flutter characteristics, spring moments, and theoretical results are provided.

Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.

Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.

From Summary: "NACA research on afterburners for turbojet engines during the past 5 years is summarized. Although most of this work has been directed toward the development of specific afterburners for various engines rather than toward the accumulation of systematic data, it has, nevertheless, provided a large fund of experimental data and experience in the field. The references cited present over 1000 afterburner configurations and some 3500 hours of operation. In the treatment of the material of this summary, the principal effort has been to convey to the reader the "know-how" acquired by research engineers in the course of the work rather than to formulate a set of design rules."

Memorandum presenting the effects of variations in cooling-passage geometry on the relations between heat flow and temperature drops within liquid-cooled turbine blades. Wall thicknesses, blade section depths, and cooling-passage sizes, shapes, and spacings were varied experimentally on a simple electric analog on which are simulated rectangular sections of blades. Results are presented in terms of temperature differences between the cooled-surface temperature and average heated-surface temperature, minimum heated-surface temperature, maximum heated-surface temperature, and maximum temperature at the centerline of the turbine blades.

Report discussing tests of a model of the Chance Vought Regulus II missile to determine the lift, static stability, dynamic stability, trim, duct information, and drag for a range of Mach numbers.

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).

Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.

Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the aerodynamic and loading characteristics of an unswept wing with a taper ratio of 0.5, an aspect ratio of 4, and NACA 65A004 airfoil sections parallel to the plane of symmetry. The results indicate that, below a Mach number of 0.94, leading-edge droop delayed the onset of leading-edge separation and moved the main wing-compression shock rearward.

An investigation of the effects of jet nozzle geometry, size of base annulus, and base bleed upon the base and afterbody pressures of a cylindrical afterbody at transonic speeds has been conducted. Sonic and supersonic conical nozzles with jet-to-base diameter ratios from 0.25 to 0.85 were investigated with a cold jet at jet total-pressure ratios up to approximately 8.0 through a Mach number range from 0.6 to 1.25. Base pressure coefficients of about -0.55 were measured for the sonic nozzles at a Mach number of 1 or greater. The jet-to-base diameter ratio had a substantial effect on the base pressure obtained on the cylindrical afterbody of this investigation. Base bleed was beneficial in increasing the base pressure under certain conditions but had little or no effect at certain other conditions.

Memorandum presenting an aircraft modification involving the incorporation of small canard surfaces into the design, which is meant to compensate for eliminating ailerons. Results of testing in the 20-foot free-spinning tunnel of dynamic models of two sweptback-wing fighter airplanes showed that canard surfaces were very effective in aiding termination of spins of these models. A discussion of the spin tests, catapult and force tests, and effect of jet-engine angular momentum is provided.

Study conducted for the U. S. Army Reactors Branch of reactors for the irradiation of food.

Report wherein acid free uranyl nitrate hexahydrate was distributed into 4-1/2 percent TBP-Amsco 125-90W and combined with various concentrations of acid in order to study the distribution of uranium and hydrolysis effects.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of the addition of one body-mounted external store, tip tanks, and several tip-mounted missile configurations on the aerodynamic characteristics in pitch of a fighter model with a low-aspect-ratio, unswept wing at Mach number 1.82. Many of the tip-mounted store configurations were found to produce increased lift-curve slopes and drag increments which decreased with increasing lift coefficient above lift coefficients of about 0.06.

Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.

Report presenting a wind-tunnel investigation at low speed in the 300 mph 7- by 10-foot tunnel to determine the effect of deflector projection on the control effectiveness of spoiler-slot-deflectors on a 30 degree sweptback wing-fuselage model equipped with either a 15-percent-chord spoiler or a spoiler-slot-deflector. Results regarding the aerodynamic characteristics, wing longitudinal characteristics, rolling-moment characteristics, and pressure distributions are provided.

Report presenting an investigation in the high-speed tunnel using the transonic bump technique in order to study the effectiveness of full-span flap-type controls on 31 unswept rectangular wings. Results regarding lift-curve slope, flap-effectiveness parameter, and the agreement between predicted and experimental results are also provided.

Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.

Report presenting results of a flight investigation of a radar fire-control system installed in a fighter airplane. Some of the factors included in the radar evaluation are "noise" of the steering dot, lack of target-attitude information, and sensitivity and linearity of the display.

Report presenting an investigation in the stability tunnel to determine the combined effect of wing and wing-body interference on the contribution of an x-tail configuration to the low-speed rolling-stability derivatives of an airplane model with an unswept midwing and to indicate the change due to roll in the local flow angularity at a number of stations across the tail surfaces for one-half of the x-tail. Results regarding the static longitudinal characteristics, steady-roll characteristics, and angularity measurements are provided.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60 degree delta-wing-fuselage model equipped with double slotted and extended double slotted flaps. The effects of a canard on the loads of the wing with the extended double slotted flaps are also determined.