From Introduction: "The present report gives results at a Mach number of 4.04 of the part of the program concerned with flap controls at Mach numbers from 1.62 to 6.9."

From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."

Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.

Report discussing the division of load among the wing, fuselage, and tail for several aircraft configurations at subsonic and supersonic speeds. The load that each component carries at various Mach numbers and angles of attack is described.

The object of this investigation was to determine the effect of increasing the carburetor pressures from 30 to 40 inches of mercury, at compression ratios from 3.5 to 7.5, on the power, on the maximum cylinder pressures, on the fuel consumption, and on the other performance characteristics of an engine. A roots-type aircraft-engine supercharger was used to maintain the desired carburetor pressure.

Memorandum presenting an investigation of the effects of higher degrees of forming in biaxial stretch-forming of polymethyl methacrylate to about 50-percent strain. Sheets of commercial cast polymethyl methacrylate were hot-stretched approximately 100 and 150 percent, respectively, and tests were conducted on this material and on unstretched cotton material. Results regarding the standard tensile tests, stress-solvent crazing, surface abrasion tests, and x-ray diffraction patterns are provided.

Abstract: "Variations in receiver slot design produce changes in quantity and quality of product and recycle, not only instantaneously, but also as a function of time in approaching equilibrium. The case of fixed feed concentration and fixed inventory of Uranium is described here for standard and Dip-Lip wider R slot receivers. The effects of the two types of receivers on recycle and product X and W concentrations, X production rate, plant X utilization efficiency, integrated X production and effective mass output are shown graphically."

Report presenting an investigation to determine the effects of plan-form taper on the aerodynamic characteristics of a series of symmetrical, unswept wings with thicknesses of 8-percent chord. The wings were tested with four different bodies of revolution over a range of Mach numbers. Results regarding the lift, drag, pitching-moment, lift-curve slope, lift-drag ratio, and pitching-moment curve are provided.

The leak detector system consists of one gas pressurized reservoir containing heavy water, a tubing manifold connecting the pressurizer to six separate lines each connected to one of the flanges, tubing lines leading from the second hole on each of three flange pairs (dome and heat exchanger flanges) back into the instrument room, plus required valves and fittings. A schematic diagram of the system in included.

A connected account is given of the Possio theory of non-stationary flow for small disturbances in a two-dimensional supersonic flow and of its application to the determination of the aerodynamic forces on an oscillating airfoil. Further application is made to the problem of wing flutter in the degrees of freedom - torsion, bending, and aileron rotations. Numerical tables for flutter calculations are provided for various values of the Mach number greater than unity. Results for bending-torsion wing flutter are shown in figures and are discussed. The static instabilities of divergence and aileron reversal are examined as is a one-degree-of-freedom case of torsional oscillatory instability.

Report discusses the development and testing of a rocket-propelled test vehicle to investigate aerodynamic control effectiveness at high subsonic, transonic, and supersonic speeds. Modifications to the section thickness and wing sweepback to improve performance are also described. A description of the vehicle, instrumentation, accuracy, and evaluation of testing results is included.

Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.

Memorandum presenting an investigation of the J71-A-11 (600-B36) turbojet engine conducted in an altitude wind tunnel, and more specifically the component and overall engine performance up to the altitude limit imposed by the use of MIL-F-5624A, grade JP-4, fuel. The data were then extended to higher altitudes by the use of gaseous-hydrogen fuel. Results regarding altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.

Abstract: Field and laboratory data are presented for 161 water samples and 235 sediment samples from the Douglas Quadrangle, Arizona; New Mexico. Uranium values have been reported by Los Alamos National Laboratory in Report GJBX-69(78). The samples were collected by Los Alamos National Laboratory; laboratory analysis and data reporting were performed by Uranium Resource Evaluation Project at Oak Ridge, Tennessee.

Data collected as part of the Douglas Quadrangle in Arizona including laboratory and field data on waters and sediments.

From abstract: Results of a reconnaissance geochemical survey of the Lincoln Quadrangle are reported. Field and laboratory data are presented for 577 groundwater and 754 stream sediment samples. Statistical and areal distributions of uranium and possible uranium-related variables are displayed. A generalized geologic map of the survey area is provided, and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed.

Data collected as part of a hydrogeochemical and stream sediment reconnaissance for the Lincoln NTMS quadrangle in Kansas and Nebraska including laboratory data on well water and stream sediments as well as field data.

"Results of a reconnaissance geochemical survey of the Watertown Quadrangle are reported. Field and laboratory data are presented for 711 groundwater and 603 stream sediment samples. Statistical and areal distributions of uranium and possible uranium-related variables are displayed. a generalized geologic map of the survey is provided and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed."

From Abstract: "This Monograph contains a consistent set of tables of thermodynamic properties of a large number of diatomic hydrides, deuterides, and tritides, for the ideal gas state at one atmosphere pressure. In addition to the thermodynamic properties of the molecular gases, the tables also include thermodynamic properties for chemical reactions involving the isotopic exchange of hydrogen."

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks" (p. 1).

Abstract: "An absolute measurement of the 14.1-Mev (n, 2n) cross sections of Li-6 and Li-7 has been made using the large scintillator technique, resulting in cross sections in barns of 0.070 +/- 0.006 and 0.056 +/- 0.005 for Li-6 and Li-7, respectively."

"The magnetic properties of color centers were studied to obtain information regarding electron traps in insulators. Experiments designed to determine the equation governing the recovery of resonance after saturation were carried out. Relatively large samples were prepared by the method of additive coloration. KCl and RbCl crystals were used. Resonance saturation as a function of concentration was investigated and no significant dependence found. Measurements of the unsaturated susceptibility were made at liquid nitrogen and liquid helium temperatures. The bleaching of the F-center to form the B-band produced a different resonance. The equipment for observing the saturation and recovery of a portion of the resonance at 4 deg K is described. A theoretical examination was made of the interaction between the vibration of the ions around a negative-ion vacancy in an alkali halide and an electron trapped at that site. (M.C.G.)."

"Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hot-wire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges" (p. 1).

"The particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid are obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The assumption is made that the Prandtl-Glauert solution of the linearized or first-order iteration equation for the two-dimensional flow of a compressible fluid is known. The forms of the particular integrals, derived for subsonic flow, are readily adapted to supersonic flows with only a change in sign of one of the parameters of the problem" (p. 909).