This quarterly progress details the ongoing work of the Protective Equipment Evaluation Program at the Oak Ridge National Laboratory. Topics discussed include aerosol generation, penetration studies, particle size measurement, and an appendix with analytical methods.

This report describes the development and design of a large bakeable valve that is based on a unique seat arrangement and a novel motion seal.

Report documenting the suitability of Tennessee for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.

Report presenting a determination of the performance and flow distributions in the first, fifth, and tenth stages of a 10-stage axial-flow research compressor at design and part speed in order to study the validity of the compressor design assumptions and to show the effects of part-speed compressor operation on stage performance.

Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.

Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.

"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).

Report presenting an investigation of an all-internal conical compression inlet with annular bleed at the throat at Mach number 5.0 and zero angle of attack. Results regarding the performance of the diffuser alone, a Pitot-pressure survey of the flow leaving the diffuser, total-pressure distribution, and inlet efficiencies are provided.

Memorandum presenting several proposed-high performance aircraft that have been studied analytically and by model flight tests to define some problem areas in dynamic lateral behavior of high-speed aircraft which require specific attention. Aileron control problems and Dutch roll characteristics with and without artificial damping were considered.

Report presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Results regarding the tail-pipe temperature, engine jet thrust, and characteristics of ice formation are provided. No general conclusions can be reached from the data because the icing condition was relatively light.

Report presenting an investigation in the 300 mph tunnel to determine the low-speed stability and control characteristics and the jet-engine duct-inlet pressure recovery characteristics of a model of the Edo 142 hydro-ski research airplane. Results regarding the longitudinal stability and control, stall-control devices, alighting gear, lateral stability, directional control, lateral control, and duct pressure recovery are provided.

Report presenting testing of wing-body combinations incorporating several wing plan forms of theoretical interest at Mach numbers of 1.62, 1.93, and 2.41 in the supersonic tunnel. One triangular, one arrow, and tow diamond plan forms were tested. Results regarding minimum drag, lift-curve slope, center-of-pressure positions, drag due to lift, and lift-drag ratios are provided.

From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."

Report presenting an investigation of two types of jet controls in the 8- by 6-foot supersonic wind tunnel. One used a converging swiveled nozzle and the other was a biconvex circular-arc vane mounted in a shroud and placed downstream of a convergent nozzle. Results regarding the jet vane, swiveled nozzle, and a preliminary evaluation are provided.

Preliminary measurements of the corrosion of titanium were made in 13 M HNO3-0.05 M fluoride using 0.1 M H3BO3 as a liquid and vapor phase complexing agent. Titanium Ax-55 was attacked at average rates of 0.58 and 0.33 mils/month in the liquid and vapor. In dissolver solutions containing 0.5 and 1.0 M titanium, all rates were less than 0.1 mils/month.

From Introduction: "This Monograph, supplemented by ORNL-3207 [9], should eliminate completely the need for use of approximate formulas (e.g. those of Kotani and Ross [10]). The formulation of the problem has been summarized in sec. II. This is followed in sec. III by a discussion of the methods used in numerical calculations. Sec. IV contains a detailed explanation to facilitate the use of present tables."

From abstract: "The dissociation of acids in tertiary butyl alcohol has been studied by potentiometric, spectrophotometric, and conductimetric methods. Values for the over-all dissociation of perchloric and picric acids and several tetrabutylammonium salts were estimated by the Fuoss-Kraus treatment of conductance data. Potentiometric studies were carried out at constant ionic strength in order to minimize activity coefficient variations. An acidity scale was established from potentiometric measurements at a glass electrode, and conductance values of dissociation constants. A method was developed for the evaluation of the over-all dissociation constant of weak acids using potentiometric data for hydrogen ion activities and conductance data for the corresponding anion activities. Over-all dissociation constants are reported for perchloric acid, picric acid, 2,4-dinitrophenol, and benzoic acid. Apparent dissociation constants from potentiometric measurements at a constant ionic strength were determined for hydrobromic, nitric, hydrochloric, picric, and p-toluenesulfonic acids."

"A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-series airfoils with thickness ratios of 4, 6, and 9 percent has been conducted in the Langley airfoil test apparatus at at transonic Mach numbers between 0.8 and 1.25. The Reynolds number range for these tests varied from 2.6 x 10(6) to 2.8 x 10(6). As was expected, the airfoils exhibited a smooth transition in force coefficients from a Mach number of 1.0 to the values obtained at the higher speeds. Lift-curve slope and maximum lift-drag ratio correlated very well on a basis of the transonic similarity laws at Mach numbers above 1.0, but below that value the correlation was not good" (p. 1).

Report discussing testing of 2-percent additions of seven aromatic amines on the knock-limited performance of 28-R fuel in a CFR engine. The most effective antiknock additives are described.

From Introduction: "The present investigation was carried out for the purpose of supplementing the earlier work with information on the boundary layer under such conditions of air speed and turbulence that transition occurs and the layer is partly laminar and partly turbulent. In the work reported in reference 1, the air speed was about 12 feet per second, and it was assumed that the boundary layer remained in the laminar condition until after separation because the separation point remained fixed and the pressure distribution about the cylinder was unaffected until an air speed of 15 feet per second was reached."

From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."

"An analog computer study was made in order to investigate the inertia coupling in rolling maneuvers of an airplane configuration utilizing a variable-incidence wing for longitudinal control. A five-degree-of-freedom system of equations was used, and only one set of flight conditions was included in this study. The results, when compared to those for a conventional tail-control airplane, indicated significant advantages for the variable-incidence-wing type of control in reducing undesired dynamic effects during rolling maneuvers" (p. 1).

An investigation of the burning rates of single drops of 15 hydrocarbon and nonhydrocarbon fuels in quiescent air at room temperature and pressure. The drop burning rates were found to be proportional to drop diameter. The experimentally determined drop burning rates were in orderly agreement with those predicted by theoretical analysis, but the absolute values differed significantly.

Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane. The amplitude and frequency of pressure fluctuations were measured using an electrical pressure gage mounted on the diffuser wall at several Mach numbers and mass-flow ratios. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.