From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."

The following report provides the results of laboratory corrosion tests held to investigate the behavior of austenitic stainless steel, Type 347, in selected O.R.N.L. #1 Redox streams.

Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.

Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.

Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.

Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.

"A preliminary low-speed investigation has been made of an air scoop submerged one-half the inlet height in a depression on the surface of a simulated fuselage. Boundary-layer suction was used on the steep approach ramp to improve the internal flow. A 6-degree-included-angle diffuser with an area ratio of 1.9:1 was located behind the inlet in the model. Most of the tests were conducted with an initial turbulent boundary layer believed to approximate that which would occur on the forward part of a fuselage" (p. 1).

From introduction: "A study of the fission product activity-fixing properties of the Savannah River Project soils was undertaken by this site to provide data for the planning of the waste disposal program for the Savannah River Project."

From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel on a 0.3-scale model of the Republic RF-84F airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight tests of the airplane. The effects of high-lift and stall-control devices, horizontal tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated. For the most part, these tests were conducted at a Reynolds number of 9.0 x 10(exp 6) and a Mach number of 0.19. The results indicated that from the standpoint of stability the inlets should possess blunted side bodies. The horizontal tail located at either the highest or lowest position investigated improved the stability of the model."

From Introduction: "Data on the extent of decomposition of a sample of aluminum borohy-dride during long-term storage are presented."

Abstract: "A theoretical criterion is given for the conditions under which the ions from an ion source may be decelerated by a decelerating grid, following the accelerating grid which extracts ions from the emitter, without causing a reduction in the current supplied by the source."

Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.

From Summary: "An investigation was made to evaluate several design variations of hollow turbine blades intended for missile-engine use. In one general type, the airfoils were formed from sheet metal; in a second type, the blades were cast. The blades were operated in J47 engine at 7950 rpm turbine speed and 1260 degrees Fahrenheit tail-pipe temperature until a failure occurred or a service life of 30 hours had been attained."

Report presenting an investigation of an inlet mounted on the side of a fuselage and utilizing a horizontally oriented 14 degree ramp located at the top of the inlet at a variety of Mach numbers. The characteristics of this inlet were compared to a conventional ramp-type side inlet. Results regarding the pressure recovery and model drag coefficients, spillage drag coefficients, and thrust minus drag comparison are provided.

The flux through a given region is proportional to the total lengths of the neutron flight paths that intersect that region. The analytical Monte Carlo procedure manufactured neutron flight paths and totaled the lengths of all paths intercepted by the regions illustrated in Figure 1. The procedure was designed to utilize the various symmetries in the lattice. / Consider a portion of the lattice whose planar cross-section is shown in Figure 5. If R is the region in which the flux is to be estimated and F the fuel rod in which the neutron originated, then flight path P results in an intercepted length whose reflection in the plane is L. On the other hand flight path P' intercepts R' with length L'. R' is not the region to be studied, but a translation of the flight path P' to F' would result in the neutron intercepting R. The origin in P was arbitrary. For each neutron originating in P another could, with equal probability, have originated in P' with parallel paths. Hence consulting L' in R' towards the total flux is equivalent to starting a neutron at P'. Thus consideration of all regions symmetric to R with respect to …

Report presenting an examination of the most promising air-cooled turbine blades for conventional turbojet engines, which are convection-cooled corrugated-insert and strut-supported blades. Successful analytical methods of predicting blade temperatures have been found for both blades. Results regarding turbine-engine performance, turboprop-engine performance, performance variations with compressor-discharge air bleed, and some cooling methods are provided.

Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.

Report presenting an investigation of a total of 31 flame-holder elements that can be classified into 7 distinct types under simulated afterburner operating conditions to determine their merit and feasibility for use in a high-velocity gas stream. The results indicated that a screen-type flame holder could far exceed the velocity limits of the same size conventional V-gutter at fuel-air ratios below about 0.045.

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.